Aircraft Stability and Control Data
138
N69-31783 NASA CR-96008 AIRCRAFT STABILITY AND CONTROL DATA By Gary L. Teper April 1969 Distribution of this report is provided in the interest of information exchange and should not be construed as endorsement by NASA of the material presented. Responsibility for the contents resides in the author or organization that prepared it. Prepared under Contract No. NAS 2-4478 by Systems Technology, Inc. Hawthorne, California for Ames Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION REPRODUCED BY NATIONAL TECHNICAL INFORMATION SERVICE U.S.DEPARIMENIOFCOMMERCE SPRINGFIELD, VA. 22161
Transcript of Aircraft Stability and Control Data
N69-31783
NASA CR-96008
AIRCRAFT STABILITY AND CONTROL DATA
By Gary L. Teper
April 1969
Distribution of this report is provided in the interest of information
exchange and should not be construed as endorsement by NASA ofthe material presented. Responsibility for the contents resides inthe author or organization that prepared it.
Prepared under Contract No. NAS 2-4478 by
Systems Technology, Inc.Hawthorne, California
for
Ames Research CenterNATIONAL AERONAUTICS AND SPACE ADMINISTRATION
REPRODUCEDBY
NATIONAL TECHNICALINFORMATION SERVICE
U.S.DEPARIMENIOFCOMMERCESPRINGFIELD,VA. 22161
FOREWORD
This report was prepared under Contract NAS2-4478 between Systems
Technologg_ Inc._ Hawthorne_ California and the National Aeronautics
and Space Administration. The _SA project monitor was L. W. Taylor.
The STI project engineer was Gary L. Teper.
The author gratefully acknowledges the aid of the STI staff in
co±lecting_ interpreting_ and organizing the data. The author also
wishes to acknowledge the fine work of the STI publications department
in the preparation of this report.
Precedingpageblank iii
ABSTRACT
Data of interest to handling qualities investigators is presentedfor various current aircraft. Included are those required to obtaintransfer functions for the aircraft's response to control inputs. Wherepossible, an analytical description of the aircraft's stability augmentoris given, and also the complete flight envelope of each aircraft iscovered for its most commonconfiguration and loading. Computedtransferfunctions for various flight conditions are included.
_V
CONTENTS
I. INTRODUCTION
II. A-7A
III. A-4D
IV. F-]O6B.
v. T-38
VI. F-gA
VII. F-104 .
VIII_ F-]OSB.
IX. B-58
X. NAVION.
XI. DC-8
APPENDIX A. AXIS SYSTEMS_ SYMBOLS, AND DERIVATIVE DEFINITIONS
APPENDIX B. TRANSFORMATION OF NON-DIMg_SIONAL STABILI_£ AXIS
DERIVATIVES TO BODY AXIS
APPENDIX C. EQUATIONS OF MOTION_ TRANSFER FUNCTIONS, ANDCOUPLING NI]MERATORS . .
Page
]
3
27
49
57
67
73
81
91
99
Io9
A-I
B-]
C-]
v
SECTION I
INTRGDUC TION
The purpose of this document is to provide handling qualities investi-
gators with readily usable data on various cl_rrent aircraft. Included are
those data required to obtain transfer functLons relating the aircraft's
response to control inputs. An analytical description of the aircraft's
stability au_nentor is also given.
_or those aircraft for which complete information was available, the
folIowLng summarizes the contents and presentation:
]. A y_eneral description is gLven_ including:
4.
a. Three-view drawing and reference geometry.
b. Flight envelope.
c. Nominal configuration (weight, inertias, and c.g.
location).
d. References.
e. Basic data sources.
A block diagram of the augmentor showing feedbacks, gains, and
scheduling.
Trim angle-of-attack and elevator versus Mach number and altitude.
Longitudinal s_d lateral nondimensional stability derivatives*
versus Mach number and altitude for the trimmed nominal configu-ration.
Geometrical parameters, longitudinal and lateral dimensional
derivatives, and longitudin_ml and lateral transfer functions
for the nominal configuration at various flight conditions.
These data are usually given for body-fixed centerline axes
(body axe s ).
For the remaining aircraft, some portion of the above is presented as
dictated by the limits of the available data.
*_ese are given for the axis system of the data source.
TR-176-I I
The intention has been to makethis report completely self-consistent
insofar as symbols, nomenclature, definitions, etc. The system used is
described in three appendices. Appendix A covers axis systems, symbolsand notation, and definitions of nondimensional and dimensional stability
derivatives. Appendix B gives the axis system transformations for the
derivatives. Appendix C includes the aircraft equations of motion andtransfer functions used herein.
While complete coverage of each aircraft including only the "latest"
s_d "best" data would be desirable, the major criterion used was that the
data be immediately accessible to the author. This is why only isolated
flight conditions are given for someaircraft, and also why, as those
people more intimately familiar with each particular aircraft will recog-
nize, the data presented mayrepresent an early estimate in the design
process and perhaps the "nominal configuration" is one which never left
the drawing board. The data have been reviewed and, although not all
those presented indicate unquestionable trends, those data knownto bebased on only early "guesstimates" or showing unreasonable trends have
been deleted. As to how well the data can be expected to match the flying
aircraft_ it is assumedthat those for whomthis document is intended
know well the difficulties of obtaining derivatives from flight test data.
Every attempt has been madeto insure reliable translation, interpretation,
and transcription of the data from their source documents.
The manufacturers of the aircraft described herein can not be held
accou_itable for tile infomnation presented, nor would they be bolmd to
concur in any conclusions with respect to their aircraft which might bederived from its use.
'lYe- 176-l 2
SECTION II
A-TA
3
I
c_i NOMINAL CRUISE CONFIGURATION
Cleon Airplane
60% Fuel
W = 21,8891bsCG at 30%MGC
Ix =13,635 Slug ft 2
[y =58,966 Slug ft z
I z =67,560 Slug ft 2
Ixz =2,933 Slug ft z
REFERENCE GEOMETRY
S = 375 ft 2
c = 10.8 ft
b = 38.7ft
BodyRef.Axes
40,000
h, (ft)
20,000
FLIGHT ENVELOPE
X X
X X X X
O0 .4 . 1.2
X Tronsfer functions givenfor these flight condlHons
I) LTV Vought Aeronautics Div. Rept. No. 2-53310/5R-1981,'_,-TA Aerodynamics Data Report" 21 Moy 1965 (U)
2) LTV Vought Aeronoutics Div. Rept. No. 2-53310/5R-5121,Rev. I ,"A-7A Estimoted Flying Quollties" 20 August 1965 (C)
3) LTV Vought Aeronoutics Div. ,"Updoted A-TA Aircraft
LateroI-Directionol Cruise Device Configurotion Doto, 25 Augur 1967
BASIC DATA SOURCES
est,motes uWind Tunnel Test ond
Some LoteroI-Directionol Derivotives
Adjusted After Flight Test
PITCH AXIS
_ep _._ .5 rad _j(Ib) 57.3 Ib ' i) }-_:55s +A-7A
I
-.25 radrad/sec
152.2 rad i_
5z3 ft/sec2 I-
GZ , X = •
(ft/sec z)
1-v
ROLL AXIS
. rod p i(Ib) = 5L_ __] -L!2_iic.,_+,l (rad/sec) =-
rad _
.10 rad/sec I_
YAW AXIS
_rp
I,__-_,
aa(rcJd)
A-TB r --_.Cos2.50b(rad/sec) rR6
(red/sec)P _-J Sin 2.5 °
(red/sec)
t red I__ __+1 =-2 5 rad/se_ F
_KARI
T.E. up l°t/I
1.5
_e
(deg)
Figtu.e 11-2. A-TA [_tabilit¥ Au{_rtentation System
5
GO
(deg)
14
12
I0
8
Sea Level
..............
_f ....
2-
°6 .2
I
, ,ooof, ...........
\ _ _N35,000ft
i L i I
.4 .6 M .8 1.0 1.2
-I0
(deg)
I I,15,00Oft
Sea Level-6 "
m 4 ....
I
-2
00 .2 .4 .6
M .8 1.0 1.2
TR--]76-I _
.8
eL
.6
I15,000ft
O0 .2 .4 .6 .8 1.0M
.2
1.2
.14
.12
CD
.08
.04
06
..............SeaLe!: ¸-.2
15,000ft
\
I
.4 .6 M .8 1.0 .2
TR-176-1 7
6
....
___
, I, 55,000 ft / t
I i / 'i _ _"_15,000ft
i ! / ...., ,,b/l"1 Sea Level i
0 .2 .4 .6 M .8 1.0 1.'2
2.0
1.6
CD a
.8
4
i !i
IZ 15,00Oft
Sea Level (_
\
XXX\\,
....................... J. ................ _.J ....
(7) .: f_ ..£-
35,00Oft
1.0
\\x. ii
\
i ............ i
;.2
I
! I
--0 .... >
._J0
0o I/Q IL_
'i
!LI
i I
° I_E --_ v
o.
Od
00 o.
oo
....2" _
0 0
0
E --V
(xl
__V_L 0 0Q o. oT e_
I I
ioo
0
I
E --v
o.
00
!
.12 , t ,
.08
CL M
.04
0
-.04
I //Q 35,00Oft
............... /iI1__. I
15,000 ft _ , uu
-'080 .2
//
ea Level I-
4
.4 .6 .8 1.0 1.2M
C DM
.12 1.........
Sea Leve! _t(__,.08 - 15,000
I
.04
0
-.04 ................0 q
i
T
Oft
.4. .6 .',4 8 !0r)
.O4
0
Cm M
-.04
-.08 -
I I
Sea Level ',
\ "_' 15,000 f,
\\\
\
© ss,ooo,
i.6
-.12 - ..
i
I-'160 .2
i
4 M .8 1.0 1.2
TR-17,]-i I1
.8
.6CLB e
.4
.2
0 o .2
_.&.35.oo'o.t"" _ ' \ _.151000ft
........ T"""..
..............
0 .2 .4. .6 M .8 1.0 1.2
[ LCy.8 -.7 1.---------E_,_ -- -- ------............. i ......... 1.............. 7..................
_ -.8 ............Sea Level/_ I --'- -i ....
-I.0 ] i l
0 .2 .4 .6 M .8 1.0 1.2
-.06
-.lot-............:f--_- .............
/SeaLevel "(.D .......[C-;_- _---
-.izl i
......_-C__35_,QQQf1.....I
JI
TR- 17c7-1 13
0 .2 .4 .6 M .8 1.0 .2
Cn/_
.12
,10
.O8
.06
Sea Level
15,000 35,000 ft
li7_
mR-17<7-1 14
0 o.2 .4 .6 M ,8 1.0 1.2
-.IC_p
_3
-.4
-,5
i Sea Level
35,oo;_i__ 15,ooo.
.....
Cnp
.O6
.O4
.02
I
II
i
0
-.02
-.040
15,00Oft
t-Sea Level
l
ii135,000, ft
.2 T 'L 35,00Oft
Sea Level _'_',,,u _. ".-,. -- ,-- 4,,..C._r
I 15,00Oft1
O0-- . .4 .6 M .8 1.0 1.2
0 .2 .4 .6 M .8 1.0 .2
Cnr , _/"'_ _'_ ,. Sea Level
/'i "\t : I _| 55, O00f,\ "NI5'OOOft
-.s6--- J---_......._...........].............t-----:,--\ <- ---....!
-.40 ................. [
-.01
-.02
-.05
M
0 0 .2 z .6 .8 1.0
! ,5,ooof,p
(_._.._ I See Leve_ /
1.2
_Q -
_QR- _OL
2(Includes Spoiler Effects)
.O8
.O6
C_.8o
(')
.O2
o6
I (_.... 1
- , x,_
.2 .4 .6 M .8 1.0 1.2
TR-176-I 17
011{}_
)
.006
.004
.002
0
- .002
i']_-1'7"_;-i 1_
Cy_r
.3
.2
00
Sea Level __
i.2
.O3
.01
0 o
Sea Level
i.2
l .....
.4 .6 1.2
"-'_ 35,000 ft
M .8 1.0
TR-1yC-I i9
!
!
PO0
!
I, IV
!
0
!
boo
!b
!
b_b
!
b0
0
0
I
-qOhI
Note:
TABLE II-A
GEOMETRICAL PARAMETERS FOR THE A-7A
Data for body-fixed centerline axis, clean flexible airplane
S = 375 ft2, b = 38.7 ft, c = 10.8 ft
W = 21,889 ib, m = 680 slugs, c.g. at 30 percent MGC
Ix = 13,635 slug-ft 2, !y = 58,966 slug-ft 2, !z = 67,560 slug-ft 2, Ixz = 2,933 slug-ft 2
BO
h (ft)
M (-)
a (ft/sec)
0 (slugs/f@)
VTo (ft/sec)
ov /2(lb/ft2)
so (aeg)
Uo (ft/sec)
Wo (ft/seo)
6eo (deg)
7o (deg)
FLIGHT CONDITION
I
I 2 3 4 5 6 7 9
0
0.S5
1,117
0.002378
0
0.6
1,117
O.OO2378
0
0.9
1,117
O.002378
15,000
0.3
I,058
0.001496
15,000
0.6
I,058
O.001496
15,000
0.9
I,058
O.O01496
15,000
1.1
I,058
O.O01496
279 670
91.5 534
11.2 2.9
274 669
54.2 33.9
-7.4 -3.35
0 0
1,005
1,200
2.1
1,004
36.8
-3.8
0
317
75.3
13.3
3O9
72.9
-8.8
0
635
301
4.0
633
44.3
-3.8
0
952
677
2.5
951
41.5
-3.85
0
1,164
1,OLO
2.9
1,163
58.9
-4.95
o
8
35,000
0.6
973.3
o. 000736
584
126
7.Y
579
76.2
-5.4
0
35,000
0.9
973- 3
O.000736
876
283
3.8
874
58. I
--a._
0
_" 0_-
O9 LO0"0--
6C_'0-
C9 Looo" o-
0C5L0"0-
"_'66-
__0" O--
LO'L--
L9"9
C6LO'O-
9LCO'O
6"0
000 c_C
6L'_-
C_9ooo" o
oCC" O-
LLLOOO'O-
LL_O0"O--
_'C_-
_6C0"0--
_'_-_-
_?_oo'o
L_'L-
_000"o+
6_90"0-
O_-
C_Co'o
L'Lfr-
_6LOO'O--
£0"L--
o9_ooo'o-
_6_o'o-
6o_-
6£_oo'o
6"gL--
_OLO0"O
969"O--
OL_OOO'O--
CRL0"0-
9"66-
?_0"0--
_'?-
CgLO0"O
o_" o-
9£ LO00" 0--
£££oo" o-
9"C_-
£ _9o" o.-
9" 9Y-
9L LO0"O
L_" L--
oLCooo" o-
_o_o" o--
9"0{-
£C LO0"O
LL'L-
9oCooo" o-
_C_o'o-
_'o--
oi'_
).CCoo"o
_C "_-
_'LL
LC_O'O--
_L'_-
CL'6
0_0" 0--
9L'L--
96"9
o_9oo" o-
_Y" o-
,fC9_
LOGO0" o
9L_-
_gLO'O
O?'C-
9"LL
_9 L-
??_oo" o-
_6" L-
+_C"T
9t[LO'O
9"0
000 c_
9%_o'o
L'L
000"_ L
6CCo'o
6"0
O00(_L
LC_o" o
9"0
000 ( _ L
797oo" o
C'O
000 _CL
_£Lo'o.-- _LO'O-
79_0"_
6"0
0
99 go" o---
9"0
0
_-_" C_-
LOGO0"o
99?'o-
99_ooo" o-
_96oo" o-
0"6_-
ULgO" o-
6LL" o-
s9 LO'O
_LO'O--
_'0
0
6 9 L 9 ff _ C _ L
_KIOI,I,!CLI_O0 J_ff-IDl'l,q
T_I_I
e9Z
nZ
_Z
_9X
z
OdO4
7
Gu_Td_T _ elqTx_lj Um_TO (sTx_ GuTiz_%u_o p_xT.j-Xpoq zoj _ m%_C :_%oz
VZ-V ZHZ EO_ _ZAIZVAI_{Z(I_IVII0!TK!Zk_CgV__IIC/IZID_I0q
E-If :EIEVg
<ob-
7
TABLE I!-C
LATERAL DIMENSIONAL DERIVATIVES FOR _ A-7A
I
-q
Note: Data are for body-fixed centerline axes, clean flexible airplane
O_I
h)
L_
h
M
Y6 a
Y6r
!
L r
!
L5 a
!
L6 r
T
N r
N'6a
!
N$ r
1
0
0.25
-0.162
-O. 00274
o.o43o
-11.9
-2. O0
I.18
5.34
2.22
1.28
-o. 087o
-0.369
o.4o2
-1.93
FL!_T CONDITION
2 3 4 5 6 8 9
0
0.6
-0.314
-0.oi 05
0.0769
-44.8
-4.46
i.15
28.4
11.4
5.74
-0. 168
-0.905
2.08
I8.61
0
0.9
-0.574
-0. 0085 7
15,000
0.3
-0.722
-O.OO15O
'_ 15,000
i
0.6
-o.187
-o.oo655
I5,000
0.9
-0.310
-0. OO691
7
I5,000
1.1
-o.435
-0. 0021 6
35,000
0.6
-0. 0847
-0. 00267I
o.o626
-98.o
-9.75
i.38
25.2
13.2
17.2
-0.379
-i .54
I .56
--11 .I
0.0307
-8.79
!
! -1.38
0.857
Ii
! 3.75
I .82EI
1 0.9484
-0.0310
-0.271
o. 28o
-1.56
o. 0537I
i -29.2
-2.73
!o .868
17.6
7.27!
I 3.12
-o.116
-0.541i
i 7.37III -5.54
t
o.o55o
-66.0
-6.79
0.843
24.1
11.2
10,2
-0.207
-0.975
1.64
-8.8O
O.0792
-71 .2
-7.31
o.859
12.5
i 7.27Ii
! 21 9i
-0.169
-1.33iI
i 1.o41t -4.83
l
0.0267
-14.9
-i .4o
o.599
7.96
3.09
I. 38
-o.o799
-o .247
0.652
--2.54
35,000
0.9
-o. 145
-0.00427
O. 0347
-3o. 6
-3. oo
o .563
14.2
6.55
4.72
-0.112
-o.455
I .01
-5.17
TABLE II-D
ELEVATOR LONGI_TDINAL _ANSF_ FUNCTION FACTORS FOR _IE A-7A
Note: Data for body-fixed centerllne axes, clean flexible airplane
FLIGHT CONDITION
I 2 3 4 5 6 7 8 9
h 0 0 0 15,000 15,OOO 15,OO0 15,000 35,000 35,000
M 0.29 0.6 0.9 0.3 "0.6 0.9 I .I 0.6 0.9
I
_L!L_
h)
8N5e
w
NB e
£N6 e
CG
tsp
6DSp
_p ; 1/Tm )
(1/Tp2)
I As
!/T81
i _/Te2
A_
!,'Tu I
i _U (!/Tu2)
i _-_ (1/%3)i
i Aw
1/Twl
I (w (1/T_2)0.%:(I/Tw 3)
/'l'nl
I/'i_2
1I%,3
Aa z
I/Tazl
I/Taz2
I/Taz3
/Taz_
0.367
1.76
o.o99_
o.156
-5.43
-0.0214
0-731
5-75
5! .i
(0.14-11)
(i. o3)
-29.o
51.7
.-o.11o
o.1o9
29.6
-o. 0624
6.21
-5 -57
-29.0
0.383
4.21
o.1oo
0.o698
-30.6
0.0122
1.79
8,3_
129
o .665
1.30
-i®
126
o.239
0.0210
165
0.00956
15.6
-14.3
-165
o.39_
6.76
o.79o
o .0472
_8.4
O. 0728
3.19
11.6
186
(I .22)
(2.28)
-318
187
(-o.oo6o3)
(0.0773)
318
o.o719
29.3
-23.3
-318
0.277
I .63
0.118
o.14o
-45. I
-0.00823
0.506
5.63
8.5
(0.369)
(0.587)
-23.8
58.9
-0.o_44
0.0990
24.5
-o. O949
5.41
-_.92
-23.8
0.316
3.15
0.0620
O.071 0
--18.8
o.oo716
1.o9
6.96
12O
o. 627
0.89o
-99.6
121
o. o5 67
0.0386
99.8
o. oo225
11 .8
-I I.o
-99.6
0.316
5.48
(o o_4_)
(-0.o513)
-41.6
o.o_43
I .97
9.13
190
0.854
1.24
-209
191
(-0.0o939)
(o.o918)
209
0 .o_31
20.0
-18.7
-209
o.185
8.81
o.589
0.0372
-4L.3
o.0422
2.02
11 .2
2_
(0.899)
(i .23)
-22O
2_
(--0.0! 31 )
(0.o53o)
221
O.Oh12
22.2
--21 . 2
--220
0.229
2.08
o.ok49
o.o75:
-8.18
-0. oo316
o.516
5.70
109
0.929
0.466
-43.2
110
-o .o553
o.o_9_
43.6
-0.o154
7.64
-7.22
-43.2
-0.oo998 -0.oo2_
-o. 0506 o. Ol 20
6.33 15.6
-5.73 -14.3
-O.00117
0.0729
25.3
-23.3
-0.00417
-o. Oh97
5.55
-5.o8
--O.OO4O5
O.OO627
11.8
-I 1 .o
-0.00147
O.'O445
20.0
--18.7
-o.OO139
o.o_25
22.2
-21.3
I
-o.OO17o
---0.0136
7.69
-7.28
0.230
3.68
(0.0616)
(-0.o9oi)
-20.2
O. 0202
0.933
6.61
1'7'7
o.753
o.719
-99._
178
o.419
0.0219
99.7
0.0173
13.2
-12.5
-99.4
-0. OO25O
o.0197
13.2
-12. 5
TABLEII-E
AILERONLATERALTRANSFERFUNCTIONFACTORSFORTHEA-TANote:Datafor body-fixedcenterlineaxes,cleanflexibleairplane
FLIGHTCC_DITIONI 2 3 4 5 6 7 8 9
h 0 0 0 15,000 15,000 15,0OO 15,0OO 35,000 _O00M O.25 O.6 0.9 0.3 0.6 O.9 I.I O.6 O.9
I
C_I
hD
A
_a
N5a
N r5 a
_a
CG
I/T s
I/T R
_a
_d
Ap
I/Tpl
_p
%
%
A r
I/Tr I
_r
_r
%
11% I (_IB)
11%2 (_)
I/T_3
I/Tay I (_ay 2)
i/T_Z2(_y2)
_&y (1/Tay 3)
(1/T_y4)
0.0462
I.62
O.237
I.81
5._
-o. o219
0.217
I.49
5.42
O.210
I.51
0.402
0.596
0.0852
2.35
-0.0O274
(o.885)
(0.667)
-233
-0.766
(o.9_3)
(o.@8)
0.0896
6.37
o.o411
4.46
0.202
2.91
28.4
0.018o
9.79
0.218
4.68
2_.2
O.O_L9
0.968
o.231
1.65
3.79
0.C_35
2.71
o.156
2.29
17.6
0.0214
6.17
0.179
3.66
. 2_.I
0.0102
7.15
o.189
5.o3
12.5
0.0319
1.28
o.114
I .81
7.96
-0.0o23_
0.217
3.05
28.5
0.217
3.05
2.08
I .12
0.287
2.29
-0.o_05
3.26
-O. 627
63.1
-7.06
2.29
5.92
-0.810
1.76
-o.oo113
O. 222
4.91
25.2
0.222
4.91
I.56
1.13
0.597
3.26
-0.O0857
7.76
-0._4
78.2
-8.61
-i .16
-i .84
(3.65)
(1o.7)
-o. 0232
0.191
I .27
3.81
0.183
1.29
0.280
O.445
o.i&6
2.18
-0.00150
(0.726)
(o._71)
-391
--0.477
(0.798)
(o._61)
o.0673
7.10
-0.oo_7
o.173
2.34
17.7
O. 173
2.34
:' 1.37
0.777
0.151
2.13
-0.0O655
2.21
-1.63
23.2
-4.16
1.32
3.12
--o.29_
.99
-0.00144
o.176
3.87
24.1
o.177
3.87
1.6_
o.9_4
o._6
2.78
-0.0o691
5.77
-o.245
86.8
-6.58
-0.596
-2.66
(3.79)
(-6.63)
-o.oo137
0.173
5.33
12.6
o.175
5.32
I.O_
0.581
0.638
3.98
-0.00216
IO.7
--0.113
188
-2.51
-0.146
-7.93
0.897
9.31
-o.0o718
0.122
I .62
8.0*
0.119
I .62
0.652
0.420
o.o198
2.03
-0.00267
0.793
0.422
-147
-I .56
o.29o
o.961
O.O_99
3.92
0.0191
2.92
0.128
2,58
14.2
-43.00241
0.124
2.64
14.3
0.124
2.6_
1.01
0.593
0.193
2.45
--0.OO427
(o.872)
(io.6)
-0.545
-0.o37_
(0.801)
(2.Zm)
-0.113
1.3o
Note:
TABLE II-F
RUDDER ]ATERAL TRANSFER FUNCI'ION FACTORS FOR THE A-7A
Data for body-fixed eenterline axes, clean flexible airplane
A
NS_r
r
N5 r
/Ts
I/T R
_d
Ap
I/_1
1/Tp2
1/Tp3
Aq)
/%1
1/%2
Ar
I/Trl
_r
%
%
i/%
I/T_2
I/%3
FLIGHT CONDITION
0
0.25
o.o462
i.62
o. 237
.81
2.22
---0. 0224
2.68
-3,38
1.84
2.78
-_.11
-I .93
I.13
o.538
I.02
O. O430
-<).0624
I .73
54.7
12.0
-O.123
i.87
-2. O0
2.60
L
0
0.6
0.0411
_ .46
O. 202
2°9i
11.4.
-0,00242
5.35
-5.31
10.9
5.37
-5.53
-8.61
4.33
0.475
o.6_z
0.0769
-0.oo199
4.45
12o
51.5
-0.0165
4-.43
_. 97
5 °92
0
0.9
0.0i80
9.75
o .218
4.6,%
13.2
-0.00117
8.31
-7.88
12.8
8.29
-8.18
-11 .I
9°87
O. 674
0.502
0.0626
0.00_266
9.76
186
62.9
-0.00502
9.57
-7.84
9.77
.
15,000
0.3
0.04:9
0.968
O. 231
I.65
18.2
-0.0237
2.33
-2.79
I.45
2.!!_
-3. _8
-I .56
0.553
0o41_
1.17
0.03c7
-0.O603
1.14
63.6
9._
-0.10_
I .27
--I .96
2.45
o.0435
2.71
o.156
2.29
7.27
©.00352
4.31
-4.45
6.89
4.3.5
-4.68
-5.54
2.35
o.473
0.735
0.0937
-©.00616
2.70
113
314.1
O. 0227
2.69
-3.69
4.3o
15,ooo
0.9
0.0214
6.17
o.175
3.66
11.2
-0.00147
6.63
-6.33
I0.8
6.64
-6.57
--8.80
6.12
o.535
0.514-I
0.0550
0.000578
6.17
170
52.3
-o. 00654
6.16
-5.78
6.80
15,000
1.1
0.0102
7.15
o. 189
5.o3
7.27
-o.oo141
5.56
-4.55
7.03
5.53
-4.76
-4.83
7.31
o.79o
o.381
0.0192
O. 00271
7.11
272
22.4
O. 000648
7.06
-8.91
1o.5
35,000
0.6
o.o319
1.28
0.114
I.81
3.09
-0.00723
3.16
-3.44
2.75
3.27
-3.79
-2.54
0.578
0.440
I .12
0.0267
-0.0178
I .32
'110
15.6
-0.0436
I.36
--2.28
2._1
35,000
0.9
0.0191
2.92
0.128
2.58
6.55
-0.00243
4.39
-4.38
6.21
4.4.3
-4.61
-5.11
2.64
0.526
o,585
o.o347
-0.0021 6
2.94
160
30.4.
-0.0107
2.97
-3.81
4.3o
TR-i (i-1 26
SECTION Ill
A-4D
27
!
I
Figo_re !Ii- ]
A-4D
NOMINAL CRUISE CONFIGURATION
Cleon Airplane
W = 17,578 Ibs
CG at25%MGC
Ix = 8090 slug- ft z
I y = 25,900 slu9- ft z
Iz = 29,200 sluo-ft z
Ixz = 1:500 stug-ft 2
BodyRef.Axes
REFERENCE GEOMETRY
S = 260 ft 2
c = 10.8 ft
b = ?_7.5ft
60,000
40,OOO
h(ft)
20,000
SL0.2
FLIGHT ENVELOPE
/Envelope for model A-4D-I
X Transfer functionsgiven forthese flight condition
REFERENCES
I) Abzug, M.J. and R.L. Faith, Aerodynamic Data for Model
A4D-I _OperotiormlFliqht Trainer, Douglas Aircraft Co.
Report ES-26104, November I, 1955
2) _Johnston,D.E. and D.H.Weir, Study of Pilot-Vehicle'Controller
Integrotion for A Minimum Complexity AFCS, Systems
Technology, Inc. Technical Report No. 127-1, July 1964
1.0
BASIC DATA SOURCES
Wind Tunnel Test
I
.-.j
I
['0
_ep
PITCH
..__+t<
I
K_ , Koz
A-4D
!
az
t Low PassFilter _"
• Scheduled for indicated airspeed
Note:
System used on the A4D-2N model only.
Control stick steering mode shown
,_x=?)
ROLL
_ap +
A-4DP
Kp" Gain in deg/deg/sec,scheduiedfor indicated air speed
(_rp
YAW
r_ LA-4Dn
r
Kr : Gain in deg/deg/sec, scheduledfor indicated air speed
Figure iii-2. A-4D _ Stability Augmentation System
14
12
ao I0(deg)
8
6
4
2
00
\\35,000 ft
\\\
.2 .4 .6 .8 1.0M
T_-I 7!]-1 _.50
.8
CL
.6
.4
.2
00
\ 55,000 ft
"Sea Le ......
.2 .4 .6 .8 1.0M
.06
.04
.02
00
i 35,000 ft
\\
/
O0 ft
•2 .4 .6 .8 1.0M
TR-17g-I 31
CLcl
5
4
5
2
0
_
All Altitudes
.2 .4M
.6 .8 1.0
1.4
1.2
1.0
0.8
]
0
/
/All Altitudes
.2 .4M
.6 .8 1.0
Tl_-176-1 32
OOO
to j
\/
i/I
O0O ,
0
i
!i i
Q 00 @ ,_- ea
¢.2
o.
c0
(DO (D
,4--.
m
oa _. _0I I
E
f
loo
!
4I
!
O t_l
i I
q
co
m
I
r_h
E_
-1.0
-I.2
-I.4
-I.6
-1.8
- 2.0
-2.20 .2 Z .6
M
All Altitudes
V
.8 I.O
Cmq
All Altitudes
!
_- 17_- I 34
000
ro
It--
00o
_i
\\\L
0
co
0_1
0,_, 0,1 0 '_
rj
00QLO
o---_00
ro
o.
\
;0,1
00
._.u_C
----C_ 0 --
r_
00C_ -----
E i
o.
cO
0o _ _. _.
I I I
_L
I
E_
/o.
¢.D
OO
I
o__
iL
o.
cO
O,1
O_" ¢.D OO
I ! I
OO
OO
OO
o.
O,I
--_ oO "_-
I
O
_,,.0
_7_0D--_7
c_
(r+,)
--.9
-I.0 .......
-I.I ..............
-12
Sea Level
15,0( ft
0 .2 .4 .6 .8 1.0M
0
-.2
-.3
0
ISea Level
15,000 ftr_ j
.m._._ " fl.mil.l_.
35,000 -
.2 .4 .6 .8 1.0M
.4
.3
.2
.I
0 0
5,000 ft
_/5,000 ftSea Level ----
.2 .4 .6M
.8 1.0
TR- ; 7__-L Y(
-.2
-.3
-.40
All Altitudes
.2 .3 .4 .5 .6M
.06
Cnp
.0,
.02
0
Seo Level/
15,000
//
t/
//
/_J/ 55,000 ft
f
/!
.2 .4 .6 .8 1.0M
_-17_-i 38
.2
C_. r
(-).,
0 o
5,ooo 15,000 ft _._Sea Level _- - _
.2 zM
.6 .8 1.0
0 .2 .4 M .6 ,8 1.0
Cn r %3
-._
-.5
Sea Level
15,000 ft¢
35,000 ft
TR-176-I 39
B
0
Li
o _I00 I'
ooo
J I- coI
JIi
ii I
o _ aJI" q
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o.
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\ o0
._I 0! 0
0
o q q
o
00
_D
O_
0
0I
0
D-
I
CY8 r .2L.I
All Altitudes
0 .2 .4 M .6 .8
0 .2 .4 M .6 .8
1.0
1.0
Cn8 r i-.06 ........ ' ...............................................
-.12 I
.06
.04
.02
0
I
seoLeve,y_,5,ooo,,_+"_,++-35,ooo,,
l I•2 .4 M .6 .8 1.0
TR-176-] 4]
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9_o L
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(-)6"0 9"0 o't 6"0 9"0 _'o gg"o _'o
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9 k 9 d _ { _ L
_OI$1CAIOO $H0!_£
oJ
8%fl_UT_ 0£0_ --: zx! _8%j-_nTs 00_98 = zI _8%J-gnIS 006_8 = XI _8%j-gnTS O_L_9 = xI
%J 9"Or = o _%g _'£8 = q _8%J 098 = S
C¢[-V _{Z HOg T_Z,I,ZKrV_IVcl_IVOI_Z2MOZO
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!
TABT__ IiI-B
LONGiTUDiI_AL DiY_SIONAL DERIVATIVES FOR THE A-4D
Note: Data are for body-fixed centerline axes, clean flexible air!o lane.
FLIGHT C OE_DIT!OI[
i 2 3 4 5 6 7 8
h c o 15, ooo _F_ ooo 15_ ooo 15, ooo 35, ooo 35, ooo
x 0.2 0.85 0.4 0.6 0.9 1.o 0.6 0.9
X w 0.0687 -O.0215 0.052 0.0422 -0.0303 --0.0251 0.0227 --0.O212
X u -0.00934 -0.0298 0.000877 -0.00938 -0.0615 -0. 1343 0.000806 -0.02_2
XSe 7.6i2 --33.942 6.068 7.396 --19.723 --15.289 6.288 --3.8_:3
Zw -0.899 -2.23 -0.535 -0. 922 -I ._78 _ -i .892 -0.3874 -0. 677I
Zu --0. 0765 -0.0982 -O. 0704 -0. 0533 --0.1174 -0. 0487 --O. 05 25 -0. 0869
Z_ e --42.08 --188.28 I --22.273 --56.68 --103.23 -94.606 --23.037 -_'3. 149
M w --0.0228 -0.0502 I -0.0131 -0.0204 -0.0379 -0.1072 --0.00908 --0.01739
M@ -0. 000763 --0. 00131 -0. 000476 --O. 000555 --0. 000902 -0. 000683 -0. 000270 -0. 000423
Xq --I. 151 --2.936 --0.670 --I .071 --i .93 k --2.455 --0. LS4 -0.876
M u 0.00232 0.00340 0.00253 0.00162 -0.00906 0.00263 0.001824 -0.00412
M_e -13.728 --63.987 -7.400 -19.256 --33.809 -7! .773 -$.096 I --14.084I
!
I
TABLE IIi-C
LATERAL DIHZFSiONAL DERIVATIVES FOR THE A-4D
Note: Data are for body-fixed centerline axes_ clean flexible airplane.
O_I
h
M
Yv
Ysa
%r
!
L5
6
T
L8 a
!
LS r
HrT
N8 a
N'8m
FLIGHT CONDITION
I 2 3 4
0 0 15,000 15,000
0.4 0.4 0.6
5
15,000
6 7 8
15,000 35,000 35,000
1.o o.6o.85 o.9 o.9
--O.2484 --0.5755 -0. 1476 -0. 228 -0.3628 -0.358 --0.1 034 --0. 1596
-0. 00582 -0. 00807 --0.00188 --0.0038 -0. 0055 6 O. 00207 -0. 000819 -0. 002763
O. 044 O. 0898 O. 02561 O. 03958 O. 0549 O. 049 O. 01791 O. 02487
--29.71 --I18. I --17.52 --35.95 -82.086
--I.813 --3.844 --I.111 --I.566 --2.503
0.8731 I.776 0.613 0.812 I.208
17.2 6£.359 8.99 21.203 39.282
8.217 37.214 k.309 10.398 22.103
13. 203 67. 279 6.706 16. 629 £2.527
-82.02 --17.557 -£0.7
--2.708 --0.761 --1.167
1.113 0.475 0.6227
44.89 8.1704 16.85
22.943 4.1675 8.717
39.85 6.352 17.31
-0.029 0.02953 -O.0348 -0.02173 0.01647 -0.0260 -0.02513 i --0.00539
I-O.5761 -1.4 -0.3432 -0.5144 -0.899 -0.88 -0.2468 -0.3893
1.4875 5.484 0.538 1.769 17.43 3.212 0.5703 1.399
-6.1953 -26.642 -3.280 -7.78 -16.36 -16.562 -3.16 -6.744
Note:
TABLEIII-D
ELEVATORLONGITUDINALTRANSFERFUNCTIONFACTORSFORTHEA-4D
Data are for body-fixed centerline axes, clean flexible airplane.
h
M
A
FLIGHT CONDITION
I 4 6 8
o.4
_sp 0.352
_sp 3.39
_p( I/Tpl ) O.0735
a_o(I/Tp2) O. 1035
Ae --13.726
N_)e I/Tel 0.0141
N_e
5e
_e
1/Te2 0.8234
2
0
0.85
0.435
7.348
o.195
0.08615
-63.98
0.0319
2.079
15,000
o.4
O. 2838
2.445
0.682
o.11o5
-7.4
0.00353
0.489
15,000
o.6
0.301
3.718
o.086
0.0747
-19.456
0.0112
0.76
5
15,000
o.9
0.3435
6.232
(-0.o6835)
(0t1101)
-33.805
0.0926
1.362
15,000
1.0
O.233
IO.857
(0.02574)
(0,1019)
-33.771
O. 1284
1.572
7
35,000
o.6
0.214
2.358
o.0859
O. 0822
-8.096
-0.o0o615
0.3591
35,000
o.9
0.2478
3.951
(-0.oso)
(0.0563)
-I4.083
0.02184
o.6259
Au 7.628 -34.074 6.076 7.4o8 -19.776 -15.32 6.293 -3.878
I/Tu I 66.931 --12.608 80.193 99.8 --2O.49 --13.172 115.28 -160.9
{u(I/Tu2) 0.584 (2.615)i 0.725 0.638 (G.98) 0.49 0.8554 (0.3383)
_u(I/Tu3) 0.8481 (3.813) 0.4926 0.8042 (3.733) 2.824 0.3595 (1.337)
Aw --42.08 --188.28 -22.274 --56.68 --103.23 -94.606 --23.034 -43.149
I/Tw I 149.77
_w(I/Tw2) 0.0614
_4_(I/Tw 3) O.O761
Ah 42.565
1/Thl 0.00122
1/Th2 11.623
139.54 313.69
0.4915
0.0546
162.98
o .o5o
21 .62
-19.671
--I03.23
-0.0172
I/_ 3 -IO.415
0.0771
22.946
--0.02081
8.454
--7.712
--22.274
325.77 357.77
(0,01471)
(0.1'127)
94.496
0.1270
24.916
-22.453
--94.606
O.2653
O.0602
Aaz -4 2.08
188.o4
0.0299
27.426
-24..502
-188.28
218.67
0.0835
203.34
-0.0238
0.0965
23.728
-0.01842
8.58o6
-8.048
0.o538
286.42
57.02
o.oo436
13.376
-I 2.282
-56.68
-0.00025I/Taz I
I/Taz 4
0.249
o.o516
42.898
0.01593
13.782
-12.892
-23.037 -43.149
-...0.0181 -.0.00227--0.0085 --0.0228 -0.00404 -0.000431 -0.000214
I/Taz2 0.00962 0.0301 0.00187 0.00835 0.05043 o.127 -0.0oo296 0.01805
I/Taz3 11.668 27.412 8.56 13.405 21.597 24.903 8.7174 13.762
--10.471 -24.484 --7.84 --12.321 --19.645 -22.437 -8.203 --12.868
TR-176-I 45
TABLE III-E
AILERON lATERAL _ANSFER FUNCTION FACTORS FOR _KE A-_D
Note: Data for bod_-fixed centerline axes, clean flexible airplane.
1 2 3
h 0 0 15,0OO
M 0.4 0.85 0.4
NIDsa
N_Sa
I/T s 0.00914 0.00568
I/T R 1.744 3.81
_d 0.112 O. 1207
_od 3.999 _.293
Ap 17.199 64.36
I/Tpl "-0.00572 -O. 0OO233
i_p 0.1149 0.121
3.986 8.845
0.00508
I.O152
o.0949
3.058
8.988
-0.01182
O. 0977
2.779
6 7 8
15,000 35,000 35,000
I.0 0.6
0.00726
2.772
FLIGHT CONDITION
4 5
15,000 15,000
0.6 0.9
o.oo599 o.oo698
I.5346 2.48
O.0885 o.0966
4.342 6.618
21.2<)3 39.282
-0.003 -0.00041
0.0923 O. 1015
4.442 8.914
21.308 39.495
O. 0924 O. 1021
4.439 8.891
i.769 17.4_
0.873 2.601
o. 0847 o. 0946
3.694 I.521
-0.0o38 -0.0o556
0.09125
6.392
44.89
-0.000211
0.0968
6.787
0.00_32
o.7o13
O. 0676
2.996
8.17
-0.0085
0.O717
2.742
o.9
o.0067
1.137
0.065
4.4o3
16.89
-0.00185
0.0669
4.553%
Acp 17.321 64.398 9.073 44.91 8.299 16.921
_(p O. 1149 O. 121 0.0991 0.0968 0.O70 0.067
3.985 8.843 2.798 6.789 2.76 4.55%
I/T r
_r
1.4875 5.484 0.5376 3.212 0.5703 I.39
0.9029 4.364 0.4868 3.054 0.3965 0.739
O. 1024 0.0571 0.0185 -O. 0646 0.O17 0.0695
3.767 2.655 4.475 2.523 4.073 3.519
--6.OO582-0.00807 -0.001883 0.oo207 -0.o00819 -O.OO276
-0.1615 (o.9834) -0.723 -0.0447 -0.2036 (0.974) -0.369
4. 156 (0.5504) 1.704 2.537 2.2264 (0.4294) 1.368
629.29 -456 134.99 3048.0 -1396.8 -838.16 197.67
--7.665 -0.7967 --2.413 --5.294 2.193 -O.4781 --2.42
-0.1975 o.3891 (-0.8875) -0.0468 -o.1843 0.3626 -o.9o3
4.248 0.6872 (2.2183) 2.54 2.266 0.4622 1.651
(-16.43) 0.0215 (1.869) (-32.14) 0.0324 0.00935 (-2.903)
(17.62_) 8.743 (4.149) 23.294 9.772 (3.712)
%
185a I/TGI(_) -2.178
1/T#2(a_) 3.287f
I/T#3 19.189
Aay --2.66
I/Tay1(_e_r2) (0.7012)
i/%2(4,y2) (1.923)
CG -0"0505
_y4(I/Tay4) 3.049(33.046)
TR-176-1 _6
TABLE III-F
RUDDER IATERAL TRANSFER FUNCTION FACTORS FOR THE A-4D
Note: Data for body-flxed centerline axes, clean flexible airplane.
h
FLIGHT CONDITION
I 2 3 4 5 6 7 8
0
M 0.4
I/T s 0.00914
I/TR I.744A
_d o.112
3.955
Ap 8.217
1/ p1 -O.005761/_ 2 3.o_ i
I/TP3 --3.O29
7.7o8
3o861/T 2 -3.211
Ar -6.199
I/_r 1.54s__r
_r 0.3075
o.7 38
% o. 4
N_Sr I/% I --0.00945
i/% 2 1.7532
I/T133 156.02
CG
0
0.85
o.o0968
3.81
O. 1207
8.293
37.21t_
-0 .ooo236
15,0(90
0.4
o.oo5o8
I .0152
0.o949
3.058
_.309
-O.0119
15,000
o.6
0.00595
I .5346
0.0885
4.342
10.398
--O.003
15,000
o.9
o.oo658
2._,8
O. o966
6.618
22. 103
-0.OOO412
15,00([)
1.0
O. 00726
2.772
0.09123
6.392
22.944
-0.000212
35,000
o.6
0.00432
0.7013
O.0676
2.996
4.167
[-0.00851
35,000
o.9
O.0067
1.137
0.065
4.403
8.717
-0.00186
4.375 2.552 3.208 4.359 4.534 2.587
-3.997 --2.6 -3.207 --4.196 --4.2rF9 -2.664 --3.79
37.028 3.795 9.936 21-9 22.83 3.678 8.379
4.376 2.642 3._ 4.378 4.539 2.729 3.797
-3.98 -2.902 -3.33 -4.227 -4.293 -2.936 -3.90
--3 •28 --I6.362
2.t_95
o.1783
0.578
o.o9_9
-0.0OO321_
2.485
303.67
-26.642
52.296
-o 86
3.815
0.363
0._63
o.09
0.00133
3.812
300.91
--I6.562
2.786
o. 1828
0.049
0.000941
2.76
342.14
51.83
-7.78
1.348
0.272
0.718
0.0396
-0.o067
1.537
212.32
-3.159
0.393
o.2o7
I.128
0oQ179
_.134
3.743
0.615
0.308
1.032
0.Iz_96
-0.0209
1.0312
153.O
-_744
0.930
0.20
0.850
A_y 20.1 89.33 10.835
I/_ayI -0.o219 -0.00154 -0.o39 -0.o147 -0.00224 -0.0326 -0.0141
1.760 1.54 2.489 2.752 0.717 1.150
0.0249
-0.0175 -0.00939
0.711 1.145
210.29 289.01
10.499 21.78_
1/Ta,y. 2
llTar
llTa
TR-176-1
5.14
-4.49
10.957
-9.526 --3._19
5.73 8.618
-7.7
9,46_
--8.63
3.733
--3.411 -4.9
SECTION IV
F- Io6B
Precedingpageblank49
i
i
_j'7
o
Figure iV- I
F -106B
NOMINAL CRUISE CONFIGURATIONCleon Airplane
W = 29,776CG at 50.5% MGC
Ix = 18,634 slug-ft 2 "_
[y 177,858slug'ft2( Body Ref.
Zz 191,236 slug-ft t ( Axes
Ixz 5,539slug "ftz )
REFERENCE GEOMETRY
S = 695 ft 2
c = 23.755 f
b = 58.15 ft
FLIGHT ENVELOPE
60,000
h(ft) /_
4o,0oo //.. j ×// ; /
2%0oo _q v., X/
M-- Maximum A/B thrust__.m Military Thrust
X Transfer functionsgivenfor theseconditions
REFERENCES :
Weyel, A.E., A.H.Terp, C.A.Lunder, Description of F-106B Aircraftto Be Used as a Variable Stability Trainer, Service Engineering Div.,
Kc_:llYel_:_Ji:_ilbiL::NE:y_;m_cs,DeC'convl_o_, A Compilation of F-106 I
Data From Various Convair Reports Contained in Letter, 14 May 1963_
I
O_!
PITCH
T_s.I
F-_36
8
F-106
YAW
F-106
$
s+l
SCHEDULED GAINS
SCHEDULED GAIN and TIME CONSTANTS
-.5
(J(I) ".4
:_ -.3"0
_-.2"0
\\
Ke
0 .2 .4 .6 .8 1.0
PreSsure Rotio,ow/Po
.6
.5 \
0 .2 .4 .6 .8 1.0
Pressure Ratio,/_H/Po
/Kp
0 200 400 600 800
Dynamic Pressure, qc, Ibs/ft2
Figure IV-2. _-_06 -- Stability Augmentatiom System
.2O
.16
.12 !
.08
.04 v
0
I
r-J
--j
I
F-JNote:
I V-A
G_OME'IRICAL PARAMETERS _ _ F-IO6B
Data are for bo_-f_l e_terlLt_ axe,,
s=695, b=38.1_, e=2_._, eoc_itlocatio=: _= 17._ , _=-3._
I ,
(--)
(rtl,,_)
p (slug,/rO)
w (_)
l_ss (s1,_s)
Ix (s1_ -ft2)
Iy (a1_-rt2)
Iz (slug "I_2)
Ixz (slug-ft 2)
xCU/C
% (aeg)
• o (eel)
eo (eel)
Uo (_l,ec)
wo (_l,,c)
FLIG_ CORDITION
20,000
0.755
1,037
o.00126?
7_
_3,000
!,090
_3,49o
195,196
219,262
4947.1
0.29
4.42
0
4._
60.6
2*
20,000
0.759
1,037
0.OO1267
39_
_0,0(0)
991
18,74_,
1_,..._00
198,707
331o.9
O.305
_.O_
0
4.O_
78_
99.4
20,000
0.799
1,o}7
o.001267
39e
28,000
870
19,8o9
177,6_9
187,119
6o19.4
0.26
3.88
0
3.88
78_
93.1
S.L.
0.2
1,116
o.00e_77
_3.2
99.3
29,500
791.9
19,800
1_,_1
9,"r"_'
o._o9
18.0
0
18.0
212
73
8,5.
0.4
1,116
0.002577
257.2
29,776
9e4.7
18,6_
177,898
191,2)6
9,9_
0._
4.9
0
4.9
_o
20,000
0.4
1,037
0.00126?
414
108.6
29,776
92_,.7
18,6_
1'r/,858
191,2_6
9,939
0._
11 .O
0
11.0
4O6
80
S,L.
0.9
1,116
0.002377
100_._
1,199
29,776
964.7
18, 6_
177, 8'38
1 91,2_6
9,9_
0._
2.0
0
2.0
1,0(0,
_6
20,000
O.9
1,057
o.001267
933
591
29,776
964.7
18,634
177,858
191,2_6
9,939
O._05
2.7
0
2.7
933
_0,000
0.9
0.ooo987
871
z_3
29,776
964.7
1 8,6_A
177,858
191,2_6
5,5)9
O._O5
9.4
0
9.4
868
82
10
20,000
1.4
1,037
o. 001267
1,4DO
1,3_'a
29,776
964.7
18,634
177,898
191,2_6
9,9_9
0._05
1.2
0
1.2
1,490
*Opt:_ del_ condition
11 12
40,000 I_0,000
1.4 2.0
0.000987 o.00o587
I,_9 1,9}6
949 1,100
29,776 29,776
964.7 _4.7
18,6_ 18,6_
177,858 177,898
191,2_6 191,2_6
9,9_9 9,9_9
0._05 O._X_5
2.70 I .2
0 0
• 2.7 1.2
I
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t-g'_-
t/t'o
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_T_
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D-AI _I_D_7
7
TABLE IV-D
RUDDER IATERAL TRANSFER FUNCTION FACTORS FOR BASIC F-I 06B
I
--4OhI
k_qkJq
MBch No., M
Altitude, hCG
Weight _
q, ib/ft _
2_iat
I/Ts
I/T R
_b
So
0.795
20,000
29
35,0oo
0._520,000
_.5_,000
o. 755
20,00026
20,000
3_
0.2
S.L.
30.525,500
59
-O.017O
1.60
2.37
0.16_
-0.01 66
2.19
2.&7
0.175
-0.0164
2.62
2.54
0.178
0.1 69
0.59e
2.42
0.162
FS I£bt C_n_ _tion
5 6 I 7i
0.4 0.4 0.9S .L. 20,000 S.L.
30.9 30.0 30.929,776 29,776 29,776
297 109 1,199
o.o_ 0.080 -o.o00
2.o9 o. 678 5.05
2.01 2.00 .4._
0.255 O. 162 0.224
P/Sr
$/5r
r/Sr
_/Sr
ay/Sr
(CG)
ay/Sr(cockpit)
A_r
i/_m
I/Tpr2(_Pr)
I/Tprs(_Pr )
A_r
I/T_r I (a_pr)
I/_m(;_)
Ar r
I/Trrl
_r(1 I_)
rr (I/Trr�)
A_r
I/TGr I
I/T_r 2
I/TOr9
Aa r
I/Tar I ((Oar)I
1/Tar2(_a r) I
I/Targ(ea r) 2
I/Tar_(_ar)2
A_ r
I/T_'rl
I/T_r 2
(a_r I )I/T_r5
£_rl)I/T_r4
7.06
-o.oo914
(i._)
(0.0693)
6.86
(I .67)
(o._)
-2.55
-o._36
(0.349)(2._)
o.o_7
-0.00111
1.96
89.9
27.9
o.o061_
1.59
-9-3O
9.9e
6.40
o.o646
-8.81
(9._)(0.890)
9.51
-0.00286
(i.72)
(o.o7oi)
9.32
(i44)(o._9)
-2.68
-o.431
(o.365)(2.71)
11 .I
-0.002T5
(I.79)(0.0736)
10.9
(I.81)
(0.0582)
-2.75
-o.427
(0.975)(9.28
2.08
-0.049
1.88
-2.64
1.9_
-2.98
1.99
-0.909
0.4_-2
2.4-8
0.21.4
6.17 2.97 19.5
-0.006 -0.015 -0._I
I .85 1.97 -0.001
-2.09 -2.54 0.569
6.09 2.81 1 9.9
-2.12 -2.4.9 -0.406
1 .85 2.02 0.5.59
-I. 63
2.18
0.680
o.419
0.0402
-0.000727
2.11
89.8
31.6
0.00696
2.00
-9._I
4.16
16.6
o.00670
-6.09
(2.99)
(o.73o)
0.0039
-o.ooo53o
2.95
81 .I
[9+.2
0.00679
2.44
-5..49
4.29
29.9
0.00699
-5.96
(3.08)
(0.66_)
0.028
-0.259
0.690
41.9
6.57
(I .02)
(o._)(1.21)
-(o.2.49)
.4.71
-0.300
0.402
-5.38
9.26
-0.792 -6.1 6
o.43o 9.97
I -74 (0. _89)
o.2_ (o._62)
0.0438 0.02.5 0.067
-0.053 -0.086 -o.oo4
2.07 0.780 9.08
90..4 6o.o 100
19.6 9.92 67 .2
-0.067 -0. 999 -0.004
2.05 0.90_ 6.89
-2.4.2 -1.1 6 -5.65
9.25 1.88 5.1 7
11.8 5.60 2.4.9
-o.o61 -o.i95 -o.oo_
-6.36 0._28 -16.1
(2.17) -5..47 (9.81)
(o.9_9) 9.99 (0.709)
0.920,000
30.5
29,776
951
-o.0o6
1.84
9.oi
o.159
11 .I
-0.782
°0.002
o.8e9
11 .0
-0.808
0.Sa3
-3.28
2.00
0.19 °
o.58e
o.920,000
30-5
29,776
223
0.001
1.0_
2.12
0.129
5.07
-o.oo9
I._4-
-I .69
.4.9_-i.7.4
i.99
-I .44
o.739
0.674
0.902
0.059
-0.0O9
I .89
o.o_9
-0.021
I .07
I0
I..420,000
30.929,776
I _952
0.01 0
4.59
4.79
o.116
7.91
-0.0009
5.19
-9.29
7.29
-9.9+
9.I_
-2.90
4.28
o.99_
0..4_
0.0_.4
-o.oo5
4._6
97.8
36.6
-0.01 0
1.89
-9.92
.4.99
16.9
-0.01 0
2.69
-8.19
5.99
105
16.2
-o.o_1.08
-2.4-4
2.88
8.03
-0.091
0.844
-9 •89
3.39
13o
34.1
-0.012
4.29
-9.97
6.16
7.89-0.012
-21 .5
8.69
11 12
1 .4 2.0
_o,ooo 14o,ooo3o.9 3o.9
29,776 29,776
_9 I,ioo
o.oiol -o.oo9
1.97 2.76
9.22 9.97
0.099 o.o7_
.4.18 5.29
-0.0OI -O.O(X)9
9._5 9.1o
-9.40 -9.98
_.I_ 9.19
-9.45 -3.61
3.37 9.10
-I .49 -I .91
I .43 2.71
.7_6 o.43o
•610 0.38_
o.o09 o.0o9
-0.004 _ -0.010
1.98 2.7.4
18,4 219
12.2 18.2
-O.Oli -o.o12
I .99 2.74
-.4-99 -5.69
9.0_ 9.99
o.78_ 2.52-0.010 -0.012
1.99 2.90
-91.o -_.4
10.9 8.94
BECTION V
_-38
Precedingpageblank _7
_-3
I
c_!
co
NOMINAL CRUISE CONFIGURATION
Clean Airplane
W = 90001bs
CG at 23%MGC
Ix = 1438 slug-ft 2
T.y = 25,874 slug-ft2 I Body
Ref.Iz = 26,779slug "ft2 Axes
[xz = 0 (assumed)
REFERENCE GEOMETRY
S = 170 ft 2
c = 7.73 ft
b = 25.25 ft
REFERENCES
I) T-38 Dynamic Stability, Norair
Report NAI 58-704,April 1959
BASIC DATA SOURCES
Wind Tunnel Tests
60,000
40,000
h(ft)
20,000
SL
//
Ii
II
0.2
FLIGHT ENVELOPE
/
Augmented Power
---- Military Power (J85-GE-5)
X Lateral transfer functionsgiven for these flight candltlon=
PITCH
__ _e T-38 8"
Io.___IO.Ss+,! I -° I
YAW
8rp 8r
SCHEDULED GAINS
o
{D
Y
C
(.D
1.8
1.61,4
Kr1.2
1.0
.8
.6
.2
00 2_ 4
Figure V-2.
\
KSo
6 8 I0 12 14 16
Impact Pressure qc ,I bs/ft2
T-38 -- Stability Augmentation System
18 20xlO0
Tk- _76-i 59
OL_L t_LL 9LOL
0<0
0 = zxI _g%J-_nI_ 000_9[ = Zl # %J-BriTs 000_0{ = £I # %@-_nIs 009#9 = xI
OVA _{_ %_ "_'o #s_nI_ O'LL{ - m ¢_ql O00_OL =
uolg_u_ljuoo _sTu_o Cs_x_ OUTl_Ogu_o p_xT_-£poq _o$ _%_6
$_-,T,,_HZ _0£ T_,V,T,ZNV_V£ qVOIH,T,ZNO,_O
V-A [_I_VZ
:_%o_
7<ob-
7
Note: Data
TABLE V-B
LATERAL NONDT}_SIONAL STABILITY DERIVATIVES FOR THE T-38
are for body fixed centerline axes, cruise configuration
I
-4GhI
Oh
h (ft)
M (--)
VT o
cy6
CY$ a
CY$ r
C_6
C_p
C_r
C_6 a
C_6 r
Cn_
Cnr,
Cnsa
Cn5 r
( f$/sec )
FLIGHT CONDITION
0
o.6
67o
-o.715
o
o.155
-o. o57
-0.320
o.080
2
o.8
893
--I.27
0
o.172
-O. 063
-0.330
o.095
3
0
1.0
1117
-i .35
0
O. 103
-0. o85
--O.275
0.110
4
25,000
O.L
4O6
-i .26
0
o.16o
-0. 097
-0. 270
o.155
5
25,000
1.0
1017
-i .35
0
0.132
-o.o86
-0.365
o.115
50,000
o.8
774
-I .26
o. 183
-o.o86
-0.335
0.140
7
50,000
1.0
968
-1.41
o.126
-o. o8o
-0.390
o.135
O. 037
o.o16
o. 262
o. o76
-0.470
o.o13
-0. 092
o.o3o
o.o_8
o.315
o.o78
o.o069
0.012
o.332
0.084
O.040
0.017
o.24o
o.085
0.026
o.o15
0.335
0.078
o.o53
O. 021
O. 286
o.o52
0.032
o.o16
o.340
O. 070
-0.435
o.o143
-0.092
-0.490
0.0126
-o. o63
--0.340
O. 0069
-0. Io3
-o.49O
0.0126
-0.o86
-o.38o
0.0149
-o. io6
-o.5oo
0.0137
-0. o86
40,000
i.25
1210
--1.20
0.097
-o. 052
-0.295
o.13o
o.o19
0.oio3
o.31o
O. 076
-o.53
0.0149
-o. 060
_9
I
-4O_
Note: Data are
TABLE V-C
LATERAL DIMenSIONAL DERIVATIVES FOR THE T-38
for body-fixed centerline axes, cruise configuration
I
o_rO
FLIGHT CONDITION
1 2 3 4 5 6 7 8
h (ft) 0 0 0 25,000 25,000 50,000 50,000 40,000
M (-) o.6 o.8 1.o o.4 _.o o.8 1.o 1.25
Yv -O.311 -0.737 --0.98 -O.151 -0.4 --0.0982 -O.137 -0.232
0 0 0 O 0 0 0 OY8a
Ysr
L !
P
L !
r
!
%a
L !
6r
I
Nr
!
N$a
0.0675
-29.69
-3.14
0.785
19.27
8. 334
17.65
o.o965
-0.597
o.876
-6.2
0.1
-58.29
-4.3]6
1.242
27.75
16.65
37.71
0.132
-0.736
1.712
-11.01
o.o75
-123.03
-4.5
1.8
9.987
17.37
62.18
O. 178
-1.037
2.36
-11.8
o.191
-8.491
-0.727
0.4]7
3.5o3
1.489
2.72
0.296
-0.1185
0.0782
-1. ] 67
0.0391
--46.24
-2.435
0.767
13.98
8.065
23.31
0.0673
-0.423
o.877
-5.984
o.o143
-9.293
-0.588
0.246
5.727
2.269
4.0
o.0118
-0.O86
0.2084
--1.482
0.0122
-13.46
--0.8544
0.296
5. 383
2.691
7.402
o.o198
-0.142
o. 298
-1.872
o.o188
-21 •73
-].286
0.567
7.941
4.305
16.77
0.0429
-0.30
0.806
-3.245
TABLE V-D
AILERON IATERAL TRANSFER FUNCTION FACTORS FOR THE T-38
Note: Data for body-fixed centerline axes, cruise configuration
h
M
A
0
o.6
I/Ts o.oo25
FLIGHT CONDITION
i/TR 3.Ol97
(d 0.121
_d 4.251
Ap 19" 273
N_ I/Tpl -0.00091
_p
%
Am 19.29
N_a I/T%(_) (o.Io8)
r
N5 a
2
0
0.8
-o.oo14
4.145
0.133
6.2
27.75
-0.0005
0
1.0
0.oo141
4.185
o.146
7-97
10.0
-o.ooo3
4
25,000
0.4
-o.o13
o.6o5
0.102
I.98
3.50
-0.012
5
25,000
1.0
o.ooo16
2.275
0.t
4.94
13.98
i-0.00082
50,000
0.8
-o. 00594
o.548
0.0527
2.187
5.727
-0.00362
50,000
1.0
-o.oo31
o.8o3
0.0585
2.847
5.383
-o.o018
8
40,000
I•25
-0.0043
1 •236
0.0705
4.151
7.941
-o.ooo554
0.108 0.12 0.127 0.0852 0.085 0.0473 0.052 0.0675
4.382 6.473 9.628 1.703 5.137 2.081 2.856 4.365
!27.78 I0.01 3.515 14.0 5-745 5.4 7.96
(0.0829)
1/%p2(_cp)(4.381)
A r 0.876
I/Tr 4.439
_r 0.267
car 2. 127
A_ --0.511
I/TPl (_#) -0. 167N5 a
1/Tl_2(_ p) 6.926
1/T_ 3
(0.127) (o.o853)
(5.135)
0.877
I.52
0.405
2.95
-O.511
--0.0843
4.90
(9-617)
2.36
4.80
0.47
1.523
-2.255
-o. o353
5. 334
(0.047)
(2.086)
0.2084
0.484
0.0827
3.19
O. 289
(o.58)
(0.283)
(o.12)
(6.471 )
1.712
5.4o5
0.423
2.113
-1 •323
-0.0832
(0.0522)
(2.856)
O. 298
o.638
0.129
2. 765
-0.0074
-0.21
t8.6247.439
(1.719)
0.782
o.535
0.192
4.345
0.446
(0.706)
(0.287)
(0.068)
(4.361)
o.8o6
1•401
0.143
1.884
-0.64
-0.o66
I.795
TR-176-I 63
Note
h
M
TABLE V-E
RUDDER LATERAL TRANSFER FUNCTION FACTORS FOR _HE T-38
Data &re for body-fixed centerline axes, cruise configuration.
FLI_IT CONDITION
I 2 3 4 5 6 7 8
0
0.8
0 25,000 29,000
I .O 0.4 I.0
0.00141 -O.013 O.0OO16
4.185 0.605 2.275
O.146 0.102 0.1
7.97 I .98 4.94
17.37 1.49
-0.0003 -0.O119
-4.522 -2.o6
4.79 I.905
17.245 i.31
-4.557 -2.293
4.79 I.994
--II.8 --I.167
4.196 O.561
0.674 O.14
0.465 0.833
0.o748 o.o191
I/Ts
I/TR
Ap
N_Sr I/Tpl
I/Tp2 (_p)
I/Tp3 ((Op)
AS
N_r I/T$I (_)
I
A r
r IITrlN5 r
r ( I/Tr2)
a_ (I/Tr3)
%
N_Sr 1/TI31
I/%2
II/T03
Aay
I/Tay I
NS_r I/Tay 2
CG I/Tay 3
I/Ta_%
O.6
0.0025 -0.OO14
3.O197 I_.145
O.121 0.133
4.251 6.2
8.33 16.65
-o.0oo92 -o.ooo5
-2.07 -o. 797
2.1.94 1 .I0
8.215 16.5
--2.11 --0.827
2.15 i.09
-6.2 -I 1.01
3.o 4.114
0.206 (0.0302)
0.309 (0.367)
0.067 0.0998
50,000
0.8
-0.OO594
50,000
1.0
-o.oo31
40,000
1.29
-0.0043
-o.ooo63 --o. ooi 6
2.994 4.075
94.93 113.63
45.24 89.16
-0.0057 -0.0018
3.89 3.799
-3.027 -6.248
-0.00212 -0.0372
4.2o5 0.65.5
161.56 72.21
83.53 7.852
-0.00447 -0.0496
4.223 o. 683
-9.098 -2.525
2.882 7.327 10.416 2.736
0.9/48
0.527
2.187
0.803
0.585
2.847
1.236
o.o7o5
4.151
8.065 2.27 2.691 4.305
-0.00082 -0.00361 --O.OO18 -0.000583
--3.311 --I.454 --I.395 (O.O081)
3.341 I.423 I .408 (0.605)
7.91 2.14 2.59 4.237
-3.372 -1.526 -1.443 !(-O.O103)
3.390 1.451 1.42 (0.608)
-9.984 -1.482 -1.872 -3.245
2.252 0.519 0.78 -0.0_71
0.373 O.11 O.196 (O.193)
0.456 0.502 0.346 (1.23)
0.0391 0.0143 0.0122 0.188
-0.0034 -O.OLO7 --0.0052 -0.oo41
2.302 0.558 0.810 1.23
159.0 117.48 64.64 178.02
39.77 11.08 11.88 22.72
-o.oo561 -0.o14 -0.0063 -o.00398
2.322 0.565 0.813 1.226
-5-987 -2.536 -3.709 -4.732
6.529 2.66 3.90 5.096
TR-176-1 64
SECTION VI
F-SA
6_
I
I
Figure Vl-]
F-5A
(_ONFIGURATIONS
GAR-8- GAR-8 on wing tips
I - Centerline Tank
150gal.tanks at W.S.85
7501b. stores at W.S. 114.5
50gaL tip tanks
T-A - as I with 50% fuel
11" - 20001b centerllne store
I000 Ib stores at W.S. 85
7501b stores at W.S.I14.5
50 gal. tip tanks
REFERENCE GEOMETRY
S = 170 ft =
b • 25.25ft
c • 7.75 ft
REFERENCE
I) Jex,H.R. and J.Nakagawa,Typical F-SA
J=_oon_tudinolAergdynomk_ Data and
Transfer Functions for 14 Conditions,
Systems Technology, Inc., Technical
Memorandum No. 239-4, March 1964
BASIC DATA SOURCES
Wind tunnel tests with corrections
made per flight test.
40,000
h(ft)
20,000
X
X w
0 w_ ° • w w
0 .5 M IJO 1.5
X Longitudinal data given at theseflight conditions,see Table E .5afor conflguratlon,_ ,and 7'e
I._=
I
PITCH
F -5A
8
YAW
F-5A
o5---2%
°'5s*' I L__
u
.c_.o
e-
£I-
SCHEDULED GAINS
I00
,o \ \\
2O
0
-_ 2O
K8 = 0.2 deg/deg/sec
K_ = 1.35 deg/deg/sec
40 60Impoct Pressure, q'c, Ibs/ft2
K I
80 IO0
Q_o..c_._o
n_
p-
SCHEDULED GAIN
1.8
1.61.4
1.2
1.0
O.8
0.6
0.4
0.2
00
\
2 4I
6 8 I0 12 14
Impact Pressure, qc, Ibs/fte
16 18 20 x I00
Figure Vi-2. F-SA -- Stabilit_ Au_memtation System
!
I
Rote : S - 170 tt 2, b - 25.2_ _, c - 7.73 t%, _o " 0.5
Data are for body-fixed stability axes.
_%BLE _q-A
_ICAL PAn ZrOR _BE F-_A
1 2
ConfiKurat1_ns 0Aa-8 G_-8
h (_t)
M
70 (_eg)
a,- :./w _o, 70
(Ibl_ 2)
w (zbs)
k0,000
0.87_
0
1.0
3.2
85O
210
1o, o00
_O,0_0
1.25
0
1.0
1.0
1210
_28
10,000
6eo(_g)
ix (_zot)
0.22 O. _c'
511 21
-I. 15 -1.80
5O,0CO 30,000
12.o 12.0
5 2 5
gAa-8 GAR-8 gAa-8+ DL_ Bz_Xe F_ps + Slate
0 20,000 0
0.875 1 ._ o.2o_
o -6o o
1.0 0.5 1.0
0.8 0 12
98o 1_-5o 228
1150 15_I0 61.9
10,0GO 10,000 10,000
O. _'_ 0.2 O. _'_
--0._-5 1.0 --4.28
_0,000 30,000 51,000
12.0 12.0 12.0
FLI_IE CCRDITI_
I
+ Flaps
0
0.286
0
1.0
12
122
19,000
0.1k
590
--6.26
_,600
11._
)0,000
0.8
0
1.0
9.0
282
17,000
0.12
--2.5'7
P,,6oo
11.2
I-A_'Dl_ Bz_ke
20,000
0.875
-60
0.5
2.8
910
521
14,000
0.1._
_55
0.52
57,900
11.2
0
0.875
0
1.0
1.2
980
1,130
I_,000
.05
-I .55
_, 700
1o.5
1o
TT E_pty
0
0.875
0
_.0
2.8
980
1,1_0
12,000
0.17
57_
--2.62
57,100
11.6
11
I-A
0
0.70
0
1.0
2.8
720
I_,000
0.15
_55
--I.13
57,900
11._
12 13 12
II II
I-A 50_ Fuel 50_ Fuel
0 0 0
0.70 0.50 0.50
0 0 0
4.0 1.0 2.0
7.0 2.2 8.0
725 570 570
I_,000 17,000 17,000
0.15 0.15 0.I_"
_ 526 528
-_.62 --2.86 -5.77
57,900 _4,400 _,_00
11. b, 11.5 11._
oC_-
0_" L--
0
g'9--
Ot "O-
oL9"o-
068OO"0
0
o_o'o
o
_£_'o
o
LL'9-
o'8
ggr.o'o
_g'O .
0
og'o
o
Ii
_t
O00_--
O_'t--
0
8"9--
Ot "0-
989 "o-
_o'o
o
o
o
_9_ "o
L_Zg'O
0
_'CS
gL'_
98"_-
_'_
L_(O"0
/Z'O
0
o_'o
o
ii
_L
OgCe"
_" L-
0
8"L-
OL"0-
o_9"o-
_6_oo'o
o
o
o
9o_'o
_8"o
o
C-g
_9"_-
o'L
LL_O'O
_g_'o
0
oL'o
0
V-I
eL
O_LL--
_-_--
0
Ot"O-
6_g"0-
_00" 0
0
0
0
0_90"0
L_8"O
0
_-g
gL'_
C_'L-
8"8
_o'o
_L'O
0
oL'o
o
Y-I
ooo_ =. _ o oo_t
"_g"t- %g" t- +_)_"_- 6_"L--
9t"0 00_'0- oLa'O- 0_0"0
L'6- _ L'6- g" _L- g'6-
L'o- L'o- o" _- og'o-
gkg"O-- gO" L-- t8%'C,- L69 O-
9gtLooo'o g_too'o LQgO0"O G69LO0"O
0 0 0 0
Q_O'O 0_0"0 0_0"0 OOt"0
0 0 0 0
96_ "o _o'o _9_o'o _g_'o
9L6"0 9'6"0 8Sg'O _'0
og'o- o o_'o ga "o-
g'g _'g g'g C'g
_9°8 _" gg° L-- _g'O Lg "8'--
8"_ 8"L g'_ 0"6
_o'o L6LO'O 8iZO'O _0"0
8_'o _Lo'o 6Lo'o gg_'O
o o o9- o
CL8"O gL_ "o gL8"o 8"o
0 0 000 '0_ 000'0_
X%c_ /,Z _@I v-I
OL 6 8 t
NOLLIG_OD _OIq_
OG6-
O_'t-
O
8"9-
GOO'O-
R_'O-
_t_O'O
_LL "0
0
0
O_'L
_05"0
0
C'g
_'C
98 "9-
_t
O_L"0
86"o
o
9_'o
o
_d_Ix +I
9
"R.,TST.Is "_'o ,zo,; pe%oea.zoo,,,
"o_'0 _:_ _I)om o]:_,s'_le _R_. %u'nooo_ o%= T aA.llg, SaAI:%'_AT,IOG.
oAt(t- o_ t
9_'L-- _O'L--
0 0t0"0-
8"9-- 6 "9-
Coo"o- o_'_
g'_'L • O- L_ ° [-
_8_oo'o g+_LtOO'O
_LL"o o
o o
o o
L_", _6LO'O-
g_L'O _09 "0
0 9"O-
_'g g-_
OOOc_-
9_'_--
o
L'6-
L'O-
Lg_'o-
GLGooo"o
o
OCO'O
o
_9_o'o
_'o
o_'o
_'C g_'_ 8_-g
"_- _o" _ g_'o-
_t o 8"0
0St "0 0_O'0 gLLO'O
_6"o _o'o _Go'o
o o9- o
_o_'o o+_-t GLS"O
0 000 tog 0
g-h'VO 8-h'vO 8-h'VO
oo_
6_'L--
OOL"0--
6-
C
9tl" _.-
9_tO0"O
0
0
0
_6"L
gt_L"0
oL'o--
g-g
8_'g
0_" !.-
0"_
L_O "o
_t "o
o
_-_.
ooo'o_
8-1_vo
GG',-" I .(v,=ll)_)'_b
o_o'o- _o
_'o_- .(_'=/0_o
_._- (_.q_)._b
_.9_'o- ..(_,=/_)
_o6ooo'o o_
o (_,=I_)_
og_o "o wco
o (w,_/_) _o
6_'o (we=It)_o
_o'_ .(_,_/:)_o
on'o w_o
_'z t (_,_I_)_o
_'i- (_) %q
8"C (_,_) %0
6Lso'o (Io
0(_ "0 "IO
o (_) oz
_/8"o w
ooo'o_ (_) q
Oh
I\D
V_-_I _}_ _ 8SAI&VAI_G XV_OIB/_HI(INO_ T_II(II%_O._Oq
E-IA
[..__H
I
_-3
I
OhI
Note :
TABLE VI-C
LONGITUDINAL DI)_SIGNAL D_IVATIVES FOR THE F-gA
Data are for body-fi_ed stability axes, quasi-steady aeroelastic corrections included.
O
2 3
GAR-8Configurations GAR-8 CAR-8 C_R-8 + Dive Brake
h (ft)
M
Xw (I/eee)
X_ (11sec)
zw (llsec)
(11se_)
%e (ftlsee21r_a)
(11sec-ft)
_& (11ft)
(I18eo)
M_ (llsec-ft)
_e (11sec2/r,_)
40,000
O .875
-0.00805
-0.01 O9
-0.754
-0.124
-I19
-0.00399
-0.0000599
-0.429
-O.O00_6e
-14.3
40,000
1.25
-O •01 R6
-o.oo589
-I .05
o.118
-IT_
-o.c_2?
0.000149
-o.9_o
-0.001 93
-e4.e
o
.879
0.0101
-0.045Z
-0.289
-599
-o.oi87
-O.0001_I
-I .9_
O.OOOO757
-73. i
20,000
1.40
0.(_o09
-0.0909
.2.22
o.4oI
-439
-o.o993
o.oo_47
-1.08
-0.00099
-63.2
9 6
GAR-8 I
+Slats + Flaps
0 0
O.20_ O.286
-o.o6o9 -o.o3oi
o.c964 -o.o_oI
-o.9o8 -o._,91
-0.276 -o.197
-24.1 -26.9
-o.oo838 -o.o138
0 0
-o.296 -o._72
o.o001 _9 O.O(X)626
-3.16 -9.91
FLIGW_ COIDITION
? 8
I-AI + Dive Brake
30,000 _,000
0.8 0.873
0.ooo_8 0.oi17
-0.0198 -0.0362
-0.521 -1.10
-o.0975 -o.71_
-78.6 -I 81
-O.00892 -0.00061
-O.O000_a7 -0.00(X)891
-0._88 -0.888
o.ooo_ -o.eo_99
-14. 9 -26.1
Note: The transfer functions given in Table E.gc) are based on the above derlvatives and the
equations of Appendix C with additional corrections msde for Inertial Bending as follows:
(®_)z_ (_)_ + Uo_(z_-z@%)- KazZ_
(_S_)R
(PC_n)z_ : (_--_)Z__ (DC_aln)_
(First coefficient)13 =_I • (first coefficient) R
where subscript IBm corrected value
R _ rigld-body + quasi-steadyaeroelastic corrections
Ka z
9 I0 II
@_ % _ Empty I-A+TT _t_
O 0 0
O.87D 0.875 o.7o
0.0e22 0.0e76 0.0178
-o.o_Yo -o.o9o9 -O.Olge
-I .86 -2.2_ -I .74
-0.0696 -0.0910 -0.0822
-_e9 -_79 -2_6
-0.0408 -0.C_93 -0.0174
-0.000109: -0.000114 -0.0OO019
-i ._8 -_ .99 -o.979
-O.0109 0.00589 0.000166
-99.8 -62.1 -91.9
: -- 0.000162 red/ft/sec 2
El II
I-A 90% Fuel _1_ Fuel
0 0 0
0.70 0.90 0.90
o.o167 0.00128 o.o14-4
-o.o_o9 -o.oi 82 -o.o919
-I .61 -1.0_ -0.828
-0. _7 -0.119 -O._'P9
_3 -99.1 -97.7
-o._ooa -o.m 7_ -o.oi 69
-0.0000199 -0.000o176 -0.000o176
-o.969 -o.667 -o.66e
o.oooe66 o.ooo_7 o.ooo_77
-_I .O -17.0 -16.7
I
OhI
TABLE VI-D
LONGiTUDL-_AL TRANSFER FUNCTIONS FOR THE F-SA
Note :
I 2
h (ft) 40,000 40,000
M o.875 1.25
_z/7o (de_) 1.olo 1.oloWt. I0,0OO I 0,000
CG 0.22 0.22
Data are for 0ody-fixed stability a_es; corrections have been made
for Inertial Bending
%p 2.29 5.84
_sp 0.266 0.121
Aa_p (I/Tpl ) 0.0_7 (-0.O721)
_p (I/Tp2) 0.0761 (0.0750)
ACe -14.6 -2_.0_T e I/_eeI 0.0995 o.oo778
I/T%2 0.703 0.885
NI _ Aue 0.970 2.26
5e I/Tuel 0.580 0.602
I/Tue2 586 525
Awe -I 21
1/Tw e I _03
N_e aWe (I/T_e2) 0.0673
_w e (I/Tve3) 0.0809
Abe
J_e I/_'_II/The2
I/_3
121
O.0O309
-8.25
8.72
54.0
0
o.oo3o9
12.8
0.o476
-18o
168
(-o.o563)
(o.o622)
180
o.o117
-12.o
12.4
120
0
0.0117
15.0
0.0559
FLIGHT CONDITION
a'
NsZ I/T_' el (°_el
I/T_'_2(;'zel
Cpi ot o
5 4 5 6 7 8 9
0 20,000 0 O 30,000 20,000 0
0.875 I •40 0 •204 0.286 0.8 0.875 0 •875
1.0/0 0.5/-60 1.0/0 1.0/0 1.0/0 0.5/-60 1.0/O
I0,000 I0,000 10,OOO 19,000 17,000 14,000 14,000
0.22 0.22 0.22 0.1 4 0.12 0.15 0.05
5.65 11.4 1.43 2.1 4 2.82 3.78 8.05
O. 325 0.128 0.286 0.I 88 0.I 82 0.270 0.215
O.0856 (-0.05465 0.197 0.147 O.O555 (-0.053O) (-0.0964)
0.257 (o.io_) 0.1o8 0.142 o.155 (0.1165 (o.1285
-80.4 -68.3 -5.16 -5.31 -14.6 -26.9 -64.0
O.0461 0.0457 0.0170 0.0225 0.0159 0.O571 O.0534
3 •3O I. 81 0.484 O. 379 O. 474 I. 03 I. 58
-6.15 -9.91 1-47 O.810 -0.O269 _ -2.19 -9.74
4.72 -I .95 0.512 0.280 0.478 2.91 4.68
-294 100 98.6 273 -17,450 -68.6 -71.4
-610 -474 -24.1 -26.9 -79.5 -186 -438
I _I 210 29. 5 62. I 146 1 51 145
0.0969 (-0.03585 0.199 0.145 0.04_2 0.0501 (-O.00410)
0.233 (0.105) 0.159 0.139 O.161 0.666 (0.0576)
610 238 24.1 26.9 79.5 93.4 438
0.0432 0.0680 -0.0718 -0. 357 0.0108 O.O661 0.0355
-19.6 -18.8 -5.59 -4.50 -8.04 -11.0 -14.3
21.7 1 9.6 3.81 4.95 8.56 12.0 15.9
355 346 13.8 55.6 84.8 11 9 255
o o.oI_ o o o (o.o538) o
0.o432 0.0499 -o.o714 -o.o536 0.01o8 (0.984) 0.0555
27.1 22.7 4.76 4.25 8.05 1_.5 20.6
0.101 0.0720 0.0871 0.O509 0.0276 0.0381 0.0379
I0
0
o.819
_.olo
12,000
o.17
7._9
0.26_
0.126
o.197
-67.0
0.O516
2.04
-14.1
9.55
-52.6
-515
129
o._-_
o.5o9
51 3
O.O5O5
-15.5
17.o
26_
o
O.O5O5
22.5
0.0618
11
0
0.70
1.0/0
14,0OO
o.15
4.81
0.285
o.o6o_
o.157
-_.6
o. 0202
1.6o
-_._8
2.79
-I 57
-246
lO5
0.0585
o.165
24.6
O.01_D
-12._
13._
I_5
0
0.01 80
18.1
0.0781
12
0
0.70
4..olo
14,000
0.15
4.95
0.262
o.115
o.129
-_2.2
o.o_8
1.46
-4.06
2.42
-i 54
-244
lO_
0.116
o.1_
244
0.025_
-11.9
12.8
124.
0
0.02_4.
17.2
0.0699
!3 14
0 0
0.50 0.5o
I .O/0 2.0/0
17,000 17,000
0._5 O._5
5.5O 5. _6
0.243 0.223
0.0852 o.118
0.1o6 0._32
-17.3 -17.o
0.01 6_ 0.0;_ "_!
O. 991 O. 724
-0.1 _ ! -_ .4_
o.9_2 0.969
-4.210 -288
-I 01
96.5
O.O82O
0.111
101
0.0110
-9.05
9.75
9_.6
O
0.O110
9-7o
0.0613
-99.7
95.6
o.116
o.I 57
99.7
c.o_ 8o
-7.98
8.67
95.2
0
o.o18o
8.6o
o.o_68
SECTION VII
F-I04
Precedingpageblank75
i
chI
Figure Vii- ]
F-104
FLIGHT CONDITIONS
ExternalTanks
Flaps
h(ft)
M
W(Ib)
xcslc
Tlp
Pylon
Leading E_e
Trailing Edge
I 2 3 4 5
Start End VMAXTakeoff Cruise Cruise VMAx Sea Level
Sea Level 30,000 30,000 30,000 Sea Level
.273 .84 1.0 1.9 1.36
24,000 23,510 14,960 15,000 15,000
.046 .040 .18 .18 .18
On
On
On
On
Clean
Clean
-3o
Cleon
Clean
-3o
Clean
Cleon
.3 °-15° .3 °
15° IS ° 0 ° 0 ° 0 °
Note: Loterol dofo not ovoiloble
REFERENCE GEOMETRY
l s : 196 ft =
b = 21.9ft
C = 9.53ft
REFERENCES
Unpubllsh_Dota
PITCH "
_epF-104
8r
ROLL"
F-104
L_s__. --_'s+l
YAW"
IF-104
TS+I
r
Figure VIi-2. F- i<)l_ -- Stability Augmentation System
T_:- 176-1 7>
Note:
TABLE VII-A
GEOMETRICALAND INERTIAL PARAMETERS FOR THE F-I04
Data are for body-fixed stability axes
S = 196.1 ft2 , c = 9.53 ft , b = 21.9 ft
h (St)
M (-)
a (ft/seo)
(slugs/ft3)
VT° (ft/sec)
_= _v2/2(ib/ft2)
w (ib)
m (slugs)
ly (slug-ft2)
Xo.g./_
s o (deg)
7o (_eg)
e o (deg)
FLIGHT CONDITION
]
TAKEOFF
Sea Level
0.273
1117
0.00238
3o5
]]0.5
24,000
746
65,000
2
START
CRUISE
30,000
o.84
995
o.0oo889
836
31o
23, 31o
724.5
64,500
3END
CRUISE
30, O00
1.0
995
O.000889
995
44O
14,960
465
56, 65O
O .O46
19.6
IO
29.6
O.040
4.0
0
4.0
0.18
2.0
O
2.0
4
Vmax
30,000
1.9
995
O .000889
1892
159o
15,ooo
466
56, 65o
o.18
1.4
o
1.4
5Vmax
SEA LEVEL
Sea Level
I.36
1117
0.00238
1519
2740
15,ooo
466
56,650
0.18
1.1
0
1.1
TR-176-1 76
Note:
TABLE VII-B
LONGITUDINAL NONDIMLmNSIONAL DERIVATIVES FOR THE F-104
Data are for body-fixed stability axes.
I
h (ft) 0
M (-) o.237
CL 1. 125
CD O. 185
4.44CL(_
eL&
C_
CL6e0.762
CDM
FLIGHT CONDITION
2 3 4
30,000 30,000 30,000
0.84 I.0
o.342
o.o365
4-.97
1 .O15
O.1375
O. 04
5.10
0
0
o.o38
I.071
CD_ I 0 0.1094 0.0255
0
CD6e
Cm_
0
--I.496
--3•44Cmc_
0
-I .319
-3.90
o.040
0
-I. 564
-4.99
1.9
o.o383
0.041
2.92
0
0
O. 6925
5
0
I.36
O. 0278
0.045
4.18
o.8035
0 O
O. 042
0
-i.255
-3 •04
0.045
0
-I .8o
-2.oo5
0 0 0 0 0Cm M
Cmct -5.615 --8.O3 --8.6O --4.59 -6.825
TR-176-I 77
TABLEVII-C
LONGITUDINALDIMENSIONALDERIVATIVESFORTHEF-IO4
Note: Data are for body-fixed stability axes.
(ft)
M(-)
Xu (I/sec)
xw (I/see)
XB e [(ft/sec2)/rad]
Zu (I/see)
z_ (-)
Zw (I/see)
ZBe [(ft/sec2)/rad]
Mu (I/see-ft)
M_ (11ft)
Mw (11sec-ft)
Mq (11sec)
MBe (I/sec2)
I
TAKEOFF
Sea Level
o.273
-0.0352
o. IO7
o
-o.214
o
-0.440
--22. I
0
--0.0005 6
-0.o156
-0. 279
--4.67
FLIGHT CONDITION
2
START
CRUISE
30,000
0.84
-0.O106
O. 0234
0
-o. 0688
0
-0.504
-85.3
O
-0.000239
-0.0142
-O.412
-17.8
3END
CRUISE
30,000
1.0
-0.0224
O. 0209
0
-o.o513
o
-0.959
-199
0
-o. o00349
-o. 0228
-o.598
-30.8
4
Vmax
30,000
1.9
-0. 0573
0.0136
0
-O. 0271
0
-1.05
-464
o
-0.000212
-0.0348
-0. 607
-57.2
5
VmaxSEA LEVEL
Sea Level
I.36
-0.115
O. 0211
0
--0. 0422
0
--3.21
-927
0
-0. 000375
-O. 107
-I. 94
--140
_-176-1 78
Note:
TABLE VII-D
E_ATOR LONGITUDINAL TRANSFER FUNCTION FACTORS FOR THE F-I04
Data are for hod ,-fixed stability axes
Mach No., M (--)
Altitude, h (ft)
CG (_ o)
Weight, W (ib)
_sp
Along
N_e
_sp
_p (I/Tpl)
A e
I/Te I
I/Te 2
I/Tu I
I/Tu2
Aw
I/Tw I
_w (1/Tw2)
a_ ( 1/T1_3 )
FLIGHT CONDITION
I
TAKEOFF
O.273
Sea Level
4.6
24,000
o.2o6
2.21
o.o932
O. 140
-_.66
o.133
o.269
-2.37
-0.0391
6.17
-22. I
_.7
o.o966
o.147
2
START
CRUISE
O.84
30,000
4.0
23,310
O.161
3.48
0. 102
o.o01
-17.8
0.01_
0.432
-2.00
I .11
-113
-85.3
175
O. 102
0.O914
3END
CRUISE
1.0
30,000
18
14,960
O. 197
4.83
0.277
O.O4O2
-30.7
0. 0237
o.812
-4.19
2.26
-85.7
-199
1.55
0.275
0.0_07
4
Vmax
1.9
30,000
18
15,0(0)
0. 126
8.16
(0.0o959)
(o.o4w)
-57. I
o .o_78
O. 767
-6.29
3.61
--62.2
-_6_
23_
(0.00967)
(0.0476)
5Vm_
SEA LEVEL
1.36
Sea Level
18
I0,000
0.220
13.0
(o.008o8)
(o.1o7)
-14o
o.115
2.51
-19.6
24.8
-_3.2
-927
231
(0.00833)
(O.107)
IITI_i
II_2
21.8
0.0185
5.21
-_.76
89.3
0.00816
9.03
-8.41
199
o. o217
11.7
-1o.7
46_
o.o971
13.9
-12.9
927
0.115
29.2
--22.7
TR-176-1 79
SECTION VIII
F-IOSB
Precedingpageblank 81
05o(3 poqsllqndun
$:10N3_13-13_i
IJ.g'll = 0
#_6"_£ = q
zl_, gg£ - S
AUI3N039 30N3_333_
suo//lPUOO $$$qi lo o/qDIIDAD lou olop IOJ_qo7 •
0 o9_ 0 0 o9t_ eSp3 ENJH!oJJ.sdOl.l
o oOZ o o oOZ ,6p3 _Jp¢_l
UOOlO UOOlO UOelO "lcNSOg,l_-_ "lO60gt,-Z UOl.(d 5UlM squo£
UOOlO UOelO UOOlO "1o60g9-1 "lD6099-1 eUllJO;UOO IOUJO;X':l
80£" 80£" eO£" g6;_" g6Z" o/so x
OL£'g£ 000'0£ 0L£';£ 0£_'1t_ O£Z'lt_ (ql)M"
I';_ ItP;_" 6" 6" 19_" IN
O00'Ote leael oos O00'G£ O00'g£ IO^Ol ooS ($_) q
xVHAqoooJddv
JeMOdj;oeNo.L
g t, £ ,Z ,I
oJcO
8goI--IL-IlIA _Y_
SNOIklQNO0 CHglldr_
I_0p--
I
E-_
PITCH •
8
_ep Se i I-_(_ _- F- 05
T K_} = Scheduled functionof impact pressure qc
ROLL'
F-105
Kp = Scheduled functionof impact pressure qc
YAW'
_rp 8r....
K_,, Kpr = Fixed gains
Ka = Scheduled functionof impact pressure qc
Ks
1.15s+l
F-105
4,
/
ay
P
Pigmre VIII-2. F-I05- gtabilit:F Aug_nent_tion System
T_- 17(;- 1 83
Note:
TABLE VIII-A
GEOMETRICAL AND INERTIAL PARAMETERS FOR THE F-105B
Inertia data are for principal axes.
S = 385 ft 2, b = 34.9 ft, C = 11.D ft
h (ft)
M (-)
a (ft/sec)
o (slugs/ft3)
VTo (ft/sec)
0v2/2(lb/ft2)
w (ib)
m (slugs)
Ix (slug-ft 2)
ly (slug-ft 2)
Iz (slug-ft 2)
Ixz (slug-ft 2)
Xc.g./_
7o (deg)
eo (deg)
FLIGHT CONDITION
I
TAKEOFF
Sea Level
o.261
1117
O. 00237
291
IO0
41,230
128o
8 _700
140,000
185,000
0
O. 295
7.4
10.0
17.4
2
START
CRUISE
35, O00
0.9
973.3
O. 00o738
875
283
41 _23o
128o
8 _700
140,000
185,000
0
O. 295
7.2
0
7.2
3END
CRUISE
C LEAN
35,0OO
0.9
973.3
o .000738
875
283
35,37o
1098
Io, 300
14o, 00o
181 ,ooo
o
o. 3o8
7.0
0
7.0
4
POWER
APPROACH
CLEAN
Sea Level
O.241
1117
0.00237
269
86
30,000
932
12_ 600
140 _000
177,000
0
o. 3o8
5.2
-5.0
0.2
5
VmaxCLEAN
40,000
2.1
968.5
o.ooo587
2030
1210
35,37O
1098
I0_ 300
140,000
181 _000
0
o, 308
3.5
0
3.5
TR-176-I 84
Note:
TABLEVIII-B
j _- ,-LONGITUDINAl, DI_[F_ _,LJlJAL DERIVATIVES FOR ThE F-IOSB
Data are for body-fixed stability axes.
1
TAKEOFF
FLIGHT CONDITION
h (ft) Se& Level
M (-) 0.261
Xu (I/sec) -0.029
Xw (1/sec) 0.0793
XSe [(ft/sec2)/rad]! 0
Zu (]/see) -0.1585!
(-) o
Zw (I/sec) --0.311
Z8 e [(ft/sec2)/rad] --17.3
M u (I/sec-ft) -0. 0000119
Mg- (I/ft) -_0.000259
M w (1/sec-ft) -0.00575
Mq (1/see) -0. 345
M6e (I/sec 2) --2.60
2
START
CRUISE
35,000
0.9
-0. oo582
O. 00693
0
-0.01386
0
-0.4
-65 •19
0
-0.000117
--o.oo819
-o .485
-12.o3
3END
CRUISE
CLEAN
35,000
0.9
-0.00565
o.o264
0
-0.05 27
o
-O .466
-75.97
O
-0. 00011 7
-O. OO4 68
-o .485
--12.03
4POWER
APPROACH
CLEAN
Sea Level
o.241
-o.0263
o.o86
o
-0.1719
0
-0.406
-I 9.88
-0. 0000101
-O. 000259
-0. 003£4
-0.319
-2.7o3
5
40,000
2.1
-0.00751
0.0132
0
-0.0265
o
-0.59o
L] 35.9
-0. oooo 198
-0.0oooo5 35
-0. O1 25 2
-0.303
-21.0
TR-176-I 85
TABLEVIII-C
LATERALDIMENSIONALDERIVATIVESFORTHEF-IO5B
Note: Data are for body-fixed stability axes, lateral data notavaiJ able for flight conditions I and 2.
Yv(
Y_r
L_ (
L_
L_
_ (N '6a
_r
I/sec)
[(_/seo)/r_d]
[(I/sec)/r&d]
I/sec 2 )
I/see)
I/see)
(I/see2)
(I/sec 2)
I/see 2 )
I/see)
I/see)
(I/see2)
(I/seo2)
FLIGHT CONDITION
3
END
CRUISE
CLEAN
35,000
0.9
-0. 1497
-0.00173
0.0234
--_1.1
-2.8
I .709
IO.71
14.37
12.39
0.324
-0.382
-i. 086
-4.71
4
POWER
APPROACH
CLEAN
Sea Level
o.241
-0.1878
-0.0021
O. 0241
-21 .5
-i. 185
i.251
3.72
2.86
4.38
O. 0729
--0.242
-0.277
-0.975
40,000
2.1
-0.213
-0. 00221
O. 0837
-I 39.8
-3.14
i.966
26.5
12.97
18.81
O. 1341
--0.386
-I. 339
-I .989
TR-176-I 86
TABLEVIII-D
ELEVATORLONGITUDINALTRANSFERFUNCTIONFACTORSFORTHEF-IOSB
Note: Data are for body-fixed stability axes.
MachNo., M (--)
Altitude h (ft
CG (¢ _)
Weight, W (ib)
Along
N_e
_e
_sp
_sp
{p
A 9
1/Te 1
1/Te 2
1/Tu1
1/T, 2
1/Tw 1
I/Th I
I/Th 2
I/Th 3
I
TAKEOFF
0.261
Sea Level
29.5
41,230
o.281
1.338
0.0297
0.1247
--2.60
0.1026
0,200
-1.367
1.o18
-17.0
-17.27
44.2
o. 0372
O. 1287
17.28
O.01292
-3.37
3.80
FLIGHT CONDITION
2
START
CRUISE
o.9
35,000
29.5
41,230
o.1819
2.71
0.1295
0.0223
-I 2.03
O.OO6]
O.355
-o.452
0.438
-696
-65.2
162
0. 129
0.0225
65.2
O. 004 66
-7.29
7.88
3END
CRUISE
CLEAN
o.9
35,000
3o.8
35,37o
0.253
2.o8
o.o631
0.0429
--I2.02
0.00891
o.433
--2.002
1.511
-55.8
-76.0
-139
0.0642
0.044
76.0
O. 00439
-7.48
8.07
4
POWER
APPROACH
CLEAN
0.241
Sea Level
30.2
30,000
0.398
0.998
O.1016
O. 1342
-2.70
0.0742
0.335
--1.708
1.266
--15.02
-19.88
36.9
o.1258
o.1435
19.88
0.01094
--3.49
3.89
5
VmaxCLEAN
2.1
40,000
3o.8
35,370
0.0893
5.o6
o.1869
0.0201
--21.0
0.00827
0.508
--1.792
2.94
-65.2
-135.9
315
o.1838
0.0204
135.9
0.00737
-12.49
12.8
TR-176-I 87
TABLEVIII-F
AILERONLATERALTRANSFERFUNCTIONFACTORSFORTHEF-IOSB
Note: Data are for body-fixed stability axes; lateraldata not available for flight conditions I and 2.
MachNo., M (--)
Altitude, h (ft)
ca (_ _)
Weight, W (ib)
_o (deg)
Alat
N_a
r
N5 a
_a
l/ms
I/T R
_a
_d
Ap
l/Tpl
_p
Ar
1/Trl
(r
_r
1/T#1
1/T#2 ([_)
3END
CRUISE
CLEAN
o.9
35,000
30.8
35,370
7.0
-0.00870
2.13
0.184
3.29
10.71
0
o. 0635
2.87
FLIGHT COND ITION
4POWER
APPROACH
CLEAN
0.241
Sea Level
3o.2
30,000
5.2
o.ooo676
1.382
O. 0545
2.13
3.72
O.OLO3
0.101
1. 674
-0. 277
-1.503
0.564
1.718
--0. 00210
O. 1427
i.655
5
Vmax
CLEAN
2.1
40,000
3o.8
35,370
3.5
0.00631
2.95
o. 1531
4.16
26.5
0
0.0744
3.44
I/T_3 (_)
-i.o86
--I.524
o.465
I.398
-133.7
--1.339
-I .3
o.6o0
1.686
-0.00174
--622
(-o.0573)
(0.276)
-0.00221
0.1379
0.658
6oi
TR-176-I 88
TABLE VIII-F
RUDDER lATERAL TRANSFER FUNCTION FACTORS FOR THE F-IOSB
Note: Data are for body-fixed stability axes; lateral
data not available for flight conditions 1 and 2.
Mach No., M (--)
Altitude_ h (ft)
Weight, W
_o (deg)
Alat
PNf_)r
_r
4r
(lb)
I/Ts
I/T R
_d
_d
%
1/%1
1/%2
1/%3
A r
1/Trl
_r
1/T_1
1/% 2
1/% 3
3END
CRUISE
CLEAN
o.9
35,000
30.8
35,370
7.0
--O.OO87O
2.13
0.184
3.29
14.37
0
-I. 109
I.014
--4.71
1.848
0.1028
0.259
0.0233
-0.0103
1.927
203
FLIGHT CONDITION
4
POWER
APPROACH
CLEAN
0.241
Sea Level
30.2
30,000
5.2
0.000676
1.382
0.0545
2.13
2.86
O.01 O3
-I. 82
I. 63
-0.975
I.4 63
-0.246
O. 838
0.0241
-0.0395
1.371
140.6
5
Vmax
CLEAN
2.1
40,000
30.8
35,370
3.5
o.oo631
2.45
o.1531
4.16
12.97
0
-I .499
I.738
-1.989
2.31
0.1601
0.342
0.00538
0.00369
2.36
37O
TR-176-1 89
?RECED_F_G PAG!
""4 NQI" _L_AED
SECTION IX
B-58
Precedingpageblank91
I
I
<D
Figure IX- ]
B-58
NOMINAL CRUISE CONFIGURATION
See Table 1T-A
50,000
40,000
h(ft)
30,000
FLIGHT CONDITIONS
X
X
20,000
I0,000
REFERENCE GEOMETRY
S = 1542 ft =
b • 56.8 ft
c • 36.2 ft
0 _"
0 ,4 .8 M 1.2 1.6 2.0
REFERENCES
I) Bright, B.E., EIIIngton,J.D.,"Applicotlon of the Limit-Cycle
Selfodoptlve Concept to the B-58 Lateral Directional
Stobillty Augmentation System'.'
Thesis, Air Force Institute of Technology, GGC/E E/64-5, May 1964
2) Anon. ,NB-58 Flight Control System", Gen. Dyn. Fort Worth, FZE- 4-049, Nov. 1962
3) Jones, L.S. ,"U.S. Bombers BI-B70" Aero Publishing Inc., 1962
SOURCE
Unknown
I
I
PITCH
8
ROLL
B-58)
L_
NOTE :
K s , K4, K5, KT, Ke...Gains Scheduledfor Moch- Number
K 2 , K 3 , K 6 , K 9 , Kjo...Goins Scheduledfor Altitude
(Air doto computer not shown)
YAW
___L
r
/
ay
The Augmentotion System for this oirplone is known to hove undergone severol modificotions. The system shown
is of 1962 vintoge os documented in GD. Convair Report FZE 4-052, Dec. 196=?, being the Iotest ovoiloble doto
Figure IX-2. B-58 -- Stability Augmentation System
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Not e :
TABLE IX-B
LATERAL NONDIMENSIONAL STABILITY DERIVATIVES FOR THE B-58
Data are for body-fixed stability axes_ cruise configuration.
I
h (ft) 0
FLIGHT CONDITION
2 3 4 5 6 7
0 0 40_ 000 44,200 30,000 40,000
0.91 2.o 0.98 i.2M (-) o.32 o.91 o.91
VTo (ft/sec) 357.3 1016 1016 880.9 1936.2 975 1161.7
Cy_ -0. 6395 -0. 6375 -0. 674 -0.7665 -0. 6275 -0.732 -0.801
CYSa O. 1511 0.08655 0.0890 O. 1790 0.0187 O. 1862 O. 1791
Cyst O.0929 O.0527 O.05725 0.0954 O.0232 O.68075 0.0545
C_ -0. 1584 -O.0551 -0.0851 -0. 1345 -0.03942 -0. 1096 -0.1158
C_p -0. 1936 -0. 1585 -0. 1576 -0.2173 -0.2317 -0.2107 -0.2238
C_r 0.04479 0.08568 0.08553 O.1102 0.07207 0.09543 O. 1071
C_$ a -0.1112 -0.04043 -0.03892 -0. 1041 -0.01782 -0.0729 -0.0010
C_6 r 0.001927 0.00729 0.007395 0.01227 0.003115 0.01328 0.0078
CuB O. 1014 O. 1242 0.0624 O. 1029 0.03207 0.0788 O. 1117
Cnp -0. 1143 -0.01082 -0.02935 -0.06118 0.01241 -0.03713 -0.04215
Cnr -0.2494 -0.2449 -0.2312 -0.2868 -0.2132 -0.2611 -0.2823
Cn6 a -0. 0405 -0. 03318 -0. 03317 -0. 0664 -0. 02038 -0. 0725 -0. 09275
Cn6 r -0. 06415 -0. 03561 -0. O35 63 --0.O633 -0.01382 -0. 053O -0. 03255
I
-4
Note:
TABLE IX-C
LATERAL DIMENSIONAL DERIVATIVES FOR THE B-58
Data for body-fixed stability axes, cruise configuration.
O_I
LOO_
(ft)
H (-)
_e
YSa
0.32
--0.09
0.0212
Y * 0.0131_r
L_ -5.828
-0.469
!
Lr
!
L5 a
0.221
--3.516
0
0.91
-0.426
o.0578
0.0382
-16.875
-I. 424
0.724
-13.19
0
0.91
--0.27
o.o356
o.o229
-23.14
-i. 238
o.6o3
-11.194
5 6 7
44,200 3O,OOO 40,000 _
2.o o.98 1.2
FLIGHT CONDITION
4
40,000
o.91
-o.o654
o.o153
0.00814
--7.575
-0.381
0.212
--5.597
0.789
1.946
-0.02
-o.159
-0.909
-1.o69
-o.o962
o.oo287
o.oo356
-8.394
-0.736
o.214
-3.965
-0.105
O. 0267
o.o116
-i i.163
-0.63
o. 278
-7.538
-0.09
0.0201
0.00613
-11.08
-0.524
O. 251
-0.953
0.748!
LSr 0.395 2.108 1.71 0.608 1.313
I_ I1858 13.71 3.818 1.895 2.317 3.202
N_ --0.0141 -0.0631 --0.I05 -O.OO473 -O.0388 --O.0293
N_ -0.222 -0.76 -0.459 -0.198 --0.231 -0.198
N{a 0.157 -4.021 -2.865 -1.413 --2.29 -2.654
f
NSr -0.669 --3.986 -2.589 -0.884 -1.614 -0.932
Note:
TABLE IX-D
AILERON IATERAL TRANSFER FUNCTION FACTORS FOR THE B-58
Data are for body-fixed stability axes, cruise configuration
h (ft)
M (-)
Np5a
r
N5a
_a
CG
I/Ts
I/TR
_a
_d
Ap
I/Tp1
_p
FLI(_IT CONDITION
i 2 3 4 9 6 7
0 o 0 40,00O 44,200 30,000 40,000
0.32 0.91 O.91 0.91 2.0 0.98 1.2
0.00426 0.0334 0.026 0.0134 0.029 0.0170.o58
0.698
0.009
i.403
-3.516
0.132
1.274
1.927
o.144
3.796
-13.19
0
1.75
0.044
2.126
--11.194
0.192
3.151
0.556
0.0O86
I .42
-9.597
0
O.0784
I•786
0.802
0.0772
I.40
-3.965
0
0.085
2.217
-I.413
0.889
o.oi65
I-98
-7.938
0.096
2.398
0.687
0.0296
I.81
-o.953
0
0.I04
5.89
-2. 654Ar 0.197 -4.021 -2.865 --0.909 -2.29
1/T R -1.148 1.881 1.498 1.002 0.983 1.082 0.934
(r 0.678 --0.213 --0.249 -0.420 --0.174 -O.331 -0.295
1.677 1.o21 0.897 0.845 o.481 0.797 0.602
0.09780.0212 0.0356 0.00287 0.0267o.o193
I/T81 (_8) 0.1624 -0.0838 -O.0941 -O.191 -O.018_ -0.073 --O.0171
I/T#2 (_B) 2.1616 1.198 0.798 0.226 0.695 0.467 0.920
I/T#3 -9.008 70.64 81.472 60.03 493.37 86.19 131.87
7.994 98.73 36.17 13.46 9.99 26.063 23.42
0.12 -0.210 -0.183 0.15 -0.02 -O.161 -0.036
I.OO9 0.69
(-6.618)
(6.883)
1/Tay 1 (_ay2)
--0.127
1.733
i/T_2 (_2) I.839
-o.892
0.89
O.35
(-2.255)
(2.927)
o.948 0.993
(-3._)
(4.896)
(-3.3)
(4.7_)
_ay3 (I/TaY3)
a_y 3 (I/Tay4)
O. 0202
0.458
(-2.8)
(3.097)
TR-176-1 97
Note:
TABLE IX-E
RUDDER lATERAL TRANSFER FUNCTION FACTORS FOR _{E B-58
Data for body-fixed stability axes, cruise configuration
h (ft) 0
0.32
0.058
M (-)
I/Ts
A I/TR
_d
r
N5r
N_r
CG
FLIGHT CONDITION
I 2 3 4
0 0
°_y 3 (1/T&y 4)
0.698
0.009
I.hO3
0.399
40,000
O.91 O.91 O.91
0.00426 0.0334 0.026
1.527
o.144
3.796
2.108
1.79
0.044
2.126
I.711
0.556
0.0086
I.42
O.789
I/TPl 0 0 0 0
I/Tp2 --2.969 --4.554 -5.859 --2.959
I/Tp3 2.713 4.065 9.365 2.818
Ar -O. 669 -3.986 -2.589 -I •069
I/Tr 0.964 I.607 I.615 0.786
_r -0.326 0.167 -0.O561 -0.317
_r 0.665 0.436 0.636 0.534
% O.0131 O.0382 0.0229 O.00814
I/T01 -0.0149 -0.00689 -0.00709 -0.008
I/T_2 0.946 I.482 I.337 0.431
I/T_3' 51.355 150.05 113.43 131.44 248.84 139-37
Aay 4.669 38.813 23.266 7.173 6.886
I/Ts.j1(_aY2) -0.0966 -0.O122 -O.O167 -0.0229 -0.0032
I/Troy2 (a_y2) 0.446 1.46 1.243 0.394 0.748
_ay3 (I/TaY3) (--1.486) (-9.179) (-4.926) (--2.492) (-4.597)
(I.828) (5-915) (5-398) (2.662) (4.788)
5 6
44,200 30,000
_.o o.98
o.o134 0.09
0.8O2 0.885
O.0772 O.0165
1.40 1.58
0.608 I.313
O 0
-3.247 -3.433
3.181 3.329
-0.884 -1.614
o.9oi I.o
-0.1o -0.2_26
0.362 0.553
0.00355 0.O116
-0 .o0171 -0.0043
0.793 0.693
7
40,000
1.2
o.o17
0.687
o.o_96
1.81
o.748
0
-3.319
3.204
-0.932
0.88
-o.255
o.518
0.00613
-0 .O0445
o.574
152.06
11.303 7.126
-0.0135 -0.0131........................
0.649 0.537
(--3.394) (--3.14)
(3.62) (3.338)
TR-176-1 98
flFDTION X
NAVION
99
I
ohI
Figure X-I
NAVION
NOMINAL FLIGHT CONDITION
h(ft) = 0 ; M = .158 ; VTo = 176 ft/sec
W = 2750 Ibs
CG at 29.5 % MAC
Tx = 1048 slug ft 2
Ty = 3000 slug ft 2
Tz = 3530 slug ft z
Ixz = 0
0REFERENCE GEOMETRY
S = 184 ft z
c = 5.7 ft
b = 33.4 ft
TABLE X-A
GEOMETRICAL PARAMETERS
FOR THE NAVION
Note: Data for body-fixed
stability axes, level flight
S (ft 2)
b (ft)
c (ft)
w (ib)
m (slugs)
e.g.(_MAC)
(sl_-_ 2)
(-_lug-_ 2)
Tz (sl_-_ 2)
_z
h (ft)
M
a (ft/see)
P (slugs/ft 3)
VTo (ft/see)
-4= VTo2/2(ib/ft 2)
cLo (deg)
7o (deg)
_8o
33.4
5.7
2,750
85.4
29.5
I,o48
3,000
3,930
0
0
O. 158
1117
0.002378
176
36.8
0.6
0
TABLE X-B TABLE X-C
LQN,GIT_INAL NONDIMEN_IONAL lATERAL NONDIMENSIONAL STABILITY
DERIVATIVES FOR THE NAVION DERIVATIVES FOR THE NAVION
Note: Data are for stability
axes
h (ft)
Data are for
stability axes
FLIGHT
CONDITION
1
0
M (--) 0.198
C L 0.41
CD O. 05
CL= 4.44
CL& 0
CLM 0
CLSe 0._5
CDc_ 0.330
CDM O
CDSe O
- .36
M o-9.96Cmq
FLIGHT
CONDITION
I
h (ft) 0
M (-) o. 158
VTo (ft/sec) 176
c_o (deg)
Cy6 -0.564
CYSa 0
CYSr O. 197
C_ -o .o74
C_p -0.410
C_r O. 1o7
C$5 a O. 1342
C_5 r O. 0118
Cn_ o.o7oI
Cr_ -o.o575
Cnr -0.125
Cn5 a -0.00346
Cn5 r -0.0717
TR-176-1 i01
TABLE X-D
LONGITUDINAL DIMENSIONAL
DERIVATIVES FOR TI-IEN&VION
FLT. COND.
Xw O.03607
Xu -0.O45]
XSe 0
Zw --2.0244
Zu -0.3 697
Zse -28.17
M w --<).04997
M_ --O.005 ]65
Mq --2.0767
M_ 0
MSe --II. 1892
TABLE X-E
LATERAL DIMENSIONAL DERIVATIVES
FOR THE NAVION
FLT. COND.
Yv
YSa
y*5r
r,f;.
-0. 2543
Lsi
L_ r
g
N '5a
--8.402
2.193
28.984
2.548
4. 495
-O. 3498
-0.7605
-O.2218
-4.597
TR-176-1 102
T I 'AB _E X-[ _' TAB[,E X-G TAB],E X-H
E ] _VA TO I_ 1,0 t'qt_I TUD IN A ]iJ
j [ rTRANSI,'I,:]_]_ NC2ION
U1ACTORS ]!'OR ']'H_J NAVION
AILERON LAI_'h",[lA.l_,'_{ANSFER
FUNCTION FACTORS
FOB TLI]!]NAVION
RUDDER libTEI{AI,T]{ANS],']:]I{
FUNCTION FACTORS
L;'ORTHE NAVION
A
N 0
u
Nb e
N w_e
flN_ e
a Z
NB e
FLT. (]ON]).
<sp o. dgP'{
"'sp 3. (;083
<p O. 0801
._ O.2137
A o --II .0114
I/THI O.0'.)231
1/T_b 1.9164
A u --1.0161
I/Tul 2.401
I/Tu2 -280.39
Aw --;'8. 171
1/% (1.98h
rw O.086u
_% o.25 63
Ah 28. 171
1/Thl --I0. I08
1/Th2 O. 01 65
I/Th3 13. 122
Aaz --28.171
I/Tazl 0
I/Taz2 --10.108
#x:0 I/Taz3 0.0165
CG i/Taz4 13.122
FLT. COND.
1/% o.oo87(;
I/TR 8. h3bA
_d o. 204
._ 2.385
Ap 28.984
N_a 1/Tpl 0
_p o. P33 6
c%o 2.136
A r _. 2218
r ]/Tr 1 --1. 253
N_)a
I/Tr2 1.543
I/mr 3 54.071
A_ 0.2218
N_Ba 1/T_ 1 0.2285
I/T_2 77.78
A
N_.P,r
F
N_',r
CG
1/T S
1/T R
md
%
11Tpl
1/Tp2
IITp 3
A r
I/T r
<r
Af{
1/Tpl
I/%_
1/T[_ 3
A_
1/Tay 1
1/Tay 2
1/% 3
I/Tay 4
VLT. COND.
o.008'( 6
8.435
0.204
2.385
2.548
0
-6.991
3. 6064
-4. 997
8. 639
0.1335
O.5345
0.0707
-0.0366
8.795
65.352
12.489
-o.o591
8.335
--3.0074
3.894
TR-176-1 103
p_EcED_NGPAGE BLANK NOT FILMED,
8F_TION XI
DC-8
Precedingpageblank_o5
P-3
I
I
FLIGRT CONDITIONS
Figure XI-]
DC-8
Flight Condition
h(ft)
W(Ibs)
[x (slug-ft 2)
Iy (slug-ft z)
Approach
0.219
190,000
3.09 x I0 s
2.94x10 s
Holdh_g
15,000
0.443
190,000
3.11xlO e
2.94x106
Cruise
:55,000
0.84
250,000
3.77x IOs
3.56x106
VNE
3:5,0000.88
250,000
3.77x 10 6
3.56x10 s
Iz (slug "ftz) 5.58 x I0 s 5.88x106 7.13 x IO s 7.13 x 106
Ixz (slug-ft =) 28x10 z -64.5x10 s 45x105 53.7 x I03
Xce IE 0.15 0.15 0.15 0.15
t StabilityAxes
REFERENCE GEOMETRY
S = 2600 ft 2
b = 142.3 ft
c = 23 ft
REFERENCES : Unpublished Dota /9
Note : Data
S = 2600 ft 2
TABLE XI-A
GEOMETRICAL AND INERTIAL PARAMETERS FOR THE DC-8
are for body-fixed stability axes
, b = 142.3 ft , c = 23 ft , Yo = 0 deg
h (ft)
M (-)
a (ft/sec)
o (s1_gs/ft3)
VTo (ft/seo)
= oV2/2 (ib/ft 2)
w (Zb)
m (slugs)
Ix (slug-ft 2)
ly (slug-ft 2)
I z (slug-ft 2)
Ixz (slug-ft 2)
XCG/C
@O
Uo
Wo
_F
(deg)
(ft/sec)
(ft/sec)
(deg)
FLIGHT CONDITION
] •
APPROACH
0
0.218
1117
o. 002378
,j
HOLD ING
15,000
0.443
1o58
0.001496
3
CRUISE
33,000
0.84
982
0.000795
243.5
71.02
190,000
59oo
3,090,000
2,940,000
5,580,000
468.2
163.97
190,000
5900
3,110,000
2,91,0,000
5,880,000
824.2
270.0
230,000
7t43
3,770,000
3,560,000
7,130,000
28,000
o.15
o
243.5
0
35
-64,5 O0
o.15
o
468.2
0
0
45,000
o.15
o
824.2
0
0
4
VNE
33,000
0.88
982
o. 000795
863.46
296.36
230,000
7143
3,770,000
3,560,000
%,130,000
53,700
0.15
0
863.46
0
0
TR-176-I 107
Note:
TABLEXI-B
LONGITUDINALNONDIMENSIONALDERIVATIVESFORTHEDC-8
Data are for body-fixed stability axes.
h 0
CLM
M 0.21$
CL 0.98
CD O. 1095
c:4_ 4.81
CLg 0
0.02
CL_ e
CD_
CDM
CD6e
Cm_
Cm_
Cm m
Cmq
O. 328
0.487
O. 0202
0
--1.478
-3.84
-o. 006
-o.ool 17
FLIGHT CONDITION
2
15,000 33_ 000
4
33,000
0.443 0.840 0.S8
0.42 0.308 0.279
0.0224 0.0188 0.0276
4.8762
0
0.048
0.328
0.212
0.00208
-0.97] 2
-1.5013
--4.10
6.7442
0
0
o. 352
0.2719
o. lOO5
0
-2 .ol 7
--6.62
-0.17
-14.6
-0.02
--o .97t 2
6.8989
0
-1.2
o. 358
0.4862
o. 3(;'.) 3
-2.413
-6.83
-0.50
-_5.2
TABLE XI-C
LATERAL NONDIMENSIONAL STABILITY DERIVATIVES FOR THE DC-8
Note: Data are for body-fixed stability axes
h (ft)
M (-)
VTo (ft/sec)
CY_ a
0
o.218
243.5
-0.87268
0
CY_r 0.18651
C_p -O.15815
C_p --O.385
C_r 0.248
C_6 a -0.08595
C_$ r 0.02189
cR_ o. 1633
Cnp -0.0873
Cnr -O.196
Cn6 a -O.O106
Cn_ r -0.08337
FLIGHT CONDITION
1D,O00
0.443
468.2
-O. 6532
o.18651
-0.137D2
-o.4]6
0.132
-0.o83o8
o.o]9195
0.12319
33,000
0.84
824.2
-O.7277
O
o.18651
-0.16732
-O.516
0.147
-0.07965
0.021086
O. 15471
33,000
0.88
863.46
-0.7449
O. 18651
-0.17362
-o .538
0.146
-0 .o79o7
0.02166
O. 16044
-0.0307 -0.0107 -0.00587
-0.161 -0.190 -0.199
-0.00354 -0.003701 -0.003999
-0.08337 -0.O8337 -O.O8337
TR-176-1 109
Note:
TABLE XI-D
LONGITUDINAL DIMENSIONAL DERIVATIVES FOR THE DC-$
Data are for body-fixed stability axes
FLIGHT CONDITION
h (ft)
M (-)
% (i/seo)
xw (I/sec)
x6e [(ft/sec2)/rad]
ZU ....(]/sec)
0
0.218
-0. 000595
-0.o2891
-o.o291
o.o629
0
-o. 25o6
19,000
o.443
-o. 000084(5
-o. oo7o7
-o. oo714
0.0321
0
-0.1 329
Zu (I/sec)
(-)
Zw (I/sec)
Z6 e [(ft/sec2)/rad]
-0. ,_)06
0
-0.6277
-lO.19
-o.1329
0
-0.75g
-23.'7
Iv]u....(I/sec-ft)
% (i/_oo-ft)
M@ (I/ft)
£w (I/sec-ft)
14q(I/see)
M8e (I/see2)
-o. 0000077
-0.0000077
-0. O01 u(_
-o. 0o8 7
-0.7924
-o. 000063
-0. o00003
-o. 00072
-o. o107
-o. 991
-3.24
33,000
o.84
O. 000D99
-o.o145
-o. OlIi
0.0043
o
-0.0735
-0.073[3
0
-o .806
-34.6
-0. 000786
-o. ooo 786
-o .o0o51
-0.0111
-0.924
-4.59
33,000
o .88
o. 000733
-0.0471
-0.04 63
-o. oP59
0
0 0622
0 0622
0
-o .845
-38.6
-o. oo254
-0. 00254
-0. 00052
---0.01 39
-I. 008
TT- 1 {'17.'-1 1 10
Note:
TABLE XI-E
IATEI_&L DIMK_SIONAL DERIVATIVES FOR THE DC-8
Data are for body-fixed stability axes
h (ft)
M (-)
Yv (I/see)
YS_ [(11sec)Irad]
YS_ [(11sec)Irad]
L_ (1/see 2)
½ (l/sec)L_ (I/see)
L5 A (I/sec 2)
L6# (I/sec 2)
N# (1/see 2)
N5 (l/_eo)N_ (I/sec)
O
N_ (i/_ee _)
N_ (1/_ec2)
1 •
0
0.218
-0.1113
0
o.0238
-i. 328
-o. 951
O. 609
-0. 726
0.1813
0.757
-0. 124
-o. 26>
-o. 0532
-0. 389
FLIGHT CONDITION
2
15,000
0.443
-0.1008
0
o.0288
-2.71
-I. 232
O. 397
-1.62
o. 392
I .301
-0. o346
-0.257
-0.01875
-o.864
3
33,000
0.84
-0.0868
0
0.0222
-4.41
-i. 181
O. 334
-2.11
0.549
2.14
-0.0204
-0.228
-0.065 2
-0.o1164
33,000
0.88
-0. o931
o
0.0233
-5.02
-I. 29
0.346
-2.3
o.612
2.43
-0.01715
--o.25
-0.0788
-1. 277
TR-176-I 111
Note :
ELEVATOR
Data are
TABLE XI-F
LONGITUDINAL TRANSFER FUNCTION FACTORS
for body-fixed stability axes
FOR _}IE DC-8
Mach No., M (-)
Altitude, h (ft)
Weight W (ib)
ZSlong
N 8_e
u
N8 e
_sp
msp
%
(I/Tpl)
(I/Tp2)
A0
I/TOl
l/T82
A m
l/Tu l
1/Tu2
A W
0.218
0
15
190,000
0.522
1.619
0.O606
O.1635
--l. 358
o. o6o5
o.535
--0.641
I.08
-35.3
-/o.19
FLIGHT CONDITION
2
0.443
15,O00
15
190, OO0
O .434
2.40
o.o31o
O. 0877
-3.22
0.01 354
O. 075
I.279
-72.7
-,'3.7
0.8h
33,000
15
230,000
o. 342
o. 241
O. 0243
-4 .>7
O. 01436
O. 7,9',;
--O.1489
o.816
-#{79
-34. G
4
0.88
33,000
15
2.50,000
0.325
3.59
(--0.0708)
(o.zo8)
-5. I
O. 0493
o. 76
I . O0
o .449
279
-38.6
w
N5 e
I/Tw 1
(I/%2)
ov (I/%3)
33.0
o.o781
o.1798
G5. o
o .o37
o. 0947
110.2
O. 13{3,
O.ODl l
-o. o361,
< ,%(O.U3_7)
(1 15.5 )
CG
A_
1/T]4_ 1
1/m 2
1/__ 3
10.19
-3.75
--0. 00182
_ .83
25.7
-5.95
-0. O0002G
7.29
Aaz -I0.19 -23.7
1/Taz I O 0
I/maz2 -3.75 -5.95
1/Taz 3 -O. O0182 --0. 000026
1/maz4 4.83 7.29
34. d
-8.24
0.O107
9.P9
-3_4.4
38.6
-8.63
o.o_31
i oo .9
O
-8.24
0.010'7'
9.59
o
o.o531
1oo.9
TR-176-1 112
Note :
TABLE XI-G
AILERON LATERAL TR_,iSFER FUNCTION FACTORS FOR 'I_{EDC-8
Data are for body-fixed stability axes
Mach No., (-)
Altitude, h (ft)
CG (_ _)
Weight, W (ib)
Alat
Np$a
r
N5 a
1/T s
1/T R
{a
_d
Ap
1/Tpl
(p
A_
A r
1/Trl
(r
_r
1/T 11/T72
1/TB3
0.218
0
15
190,000
-0.013
1.121
o.Io96
o .996
-0.725
0
0.223
0.943
-0.726
O. 223
0.943
-0.0532
O. 998
-O. 656
I .242
O.0532
-2.75
0.203
FLIGHT CONDITION
0.443
I5,000
15
190,000
O. 00649
I .329
O. 1061
1.197
-1 .62
0
o. 1554
I .166
-1.52
o. 1554
t .166
-o.o1875
1.589
-o. 727
2.23
O. 01875
3
o.84
33,000
15
230,000
O. 00404
1 .254
O. 0793
1.495
--2.11
0
O. 1072
1.515
--2.11
o. 1072
i.515
-o. 065 2
I.644
-0.392
I.323
4
0.88
33,000
15
230,000
O.00447
I.356
O.O855
I.589
-2.3o
0
O. 1094
1.620
-2.3o
o. 1o94
1.620
-o. 0788
I.757
-O. 345
I.259
o.0652
-1.036
0.291
-0. 0788
-0. 704
0.404
TR-175-I 113
Note :
TABLE XI-H
RUDDER LATERAL TRANSFER FUNCTION FACTORS FOR THE DC-8
Data are for body-fixed stability axes.
Mach No., M (-)
Altitude, h (ft)
(¢
Weight, W (lb)
Alat
NP r
q)
N_r
r
N5 r
PN6 r
I/ms
I/T R
[d
COd
Ap
I/Tpl
I/Tp2
I/T>3
A_
I I/Tqpl
I/Tep2
I
A r
I/Tr I
_r
_r
1/mpl
1/T 2
1/Tp3
0.218
0
15
190,000
-o.o13
I.121
o.Io96
o.996
0.1813
0
1. 028
-2.13
o.1813
1.o28
-2.13
-o. 389
I.124
-o. 0743
o.339
0.0238
-O.O559
1,141
16.47
FLIGHT CONDITION
2
0.443
15,000
15
190,000
0.00649
1.329
0.1061
1.197
0.392
0
i.85
-2.56
0.392
I.85
-2.56
--0.864
1.335
-O.O451
0.330
o.0288
-o, o14 7)
1.297
3o .2
0.84
33,000
15
230,000
o. 00404
i.254
o.0793
I.495
0.545
o
2.43
-3.oi
o.545
2.43
-3.oi
--1 . 165
I.276
--0.0619
o. 323
0.0222
--0.00726
1.217
52.6
4
0.88
33,000
15
230,000
O. 00447
1 .356
O. 0855
1 .D89
0.612
0
2.57
-5.15
0,612
2.57
-3.15
-1.277
1.377
-0.0475
0.323
0.0233
-0.00637
1.323
f rpp. 0
Cd
Aay
1/may 1
I/may 2
1/may 3 ( _ay)
l/may
5.79
-O.819
-4).I077
(O.994 )
(1.078)
13.hS
-O. 0347
i .535
--1.157
i.147
18.33
-0 .ot883
1 .122
--1 .418
1 ,723
20. I
-o .Ol 7146
I .231
-1.494
I .819
TR-176-1 114
APPENDIX A
AXIS SYSTEm, SYMBOLS,AND DERIVATIVE DEFINITIONS
I. .a_:T.8IB_r_TEI_B
YB,Ys,v,q
g
_XB,U,P
f v,--_/_ ............"_, _--Inerticll Ref.
ZB,W,r
XB, YB, ZB -
XS, YS, ZS -
The Body-Axis System consists of right-handed, orthogonalaxes whose origin is fixed at the nominal aircraft center
of gravity. It's orientation remains fixed with respect
to the aircraft, the XB and ZB axes being in the plane ofsymmetry. The exact alignment of XB axis is arbitrary, herein
it is taken along the body centerline reference.
The Stability-Axis System is that particular body-axis
system for which the Xs_axis is coincident with the
projection of the total steady-state velocity vector (VTo)on the aircraft's plane of symmetry. It's orientation
remains fixed with respect to the aircraft.
A-I
2. SYMBOLS
a
!
ay
az
Ia z
b
C
CG
D
g
h
Ix, ly, Iz
Ixz
jcD
ix
Iz
L
Speed of sound in air
Lateral acceleration along the Y-Body Axis
at the center of gravity (positive out right
wing)
Lateral acceleration parallel to the
Y-Body Axis at a distance ix and iz from the
c.g., _ = _ +ix_-iz_
Normal acceleration along the Z-Body Axis
at the c.g. (positive down)
Normal acceleration parallel to the Z-Body
Axis at a distance ix from the
, = a z - lx_c.g._ a z
Reference wing span
Reference chord
Center of gravity
Aerodynamic force (drag) along the total
velocity vector (positive aft)
Acceleration due to gravity
Altitude
Moments of inertia referred to body axis
Product of inertia referred to body axis
The imaginary portion of the complex
variable s = _±j_
Distance along the X-Body Axis from the
c.g. (positive forward)
Distance along the Z-BodyAxis from the
c.g. (positive down)
Rolling moment about the X-axis due to
aerodynamic torques (positive right wing
_own)
ft/sec
ft/sec 2
ft/sec 2
ft/sec 2
ft/sec 2
ft
ft
lbs
ft/sec 2
ft
slug-ft 2
slug-ft 2
rad/sec
ft
ft
ft-lb
A-2
L ibs
m
M
M
MAC
MGC
N
N
P
q
r
rRG
s
S
T.E.
u
U o
v
VT o
Aerodynamic force (lift) perpendicular
to the total velocity vector in the aircraft's
plane of symmetry (positive up)
Mass
Mach number
Pitching moment about the Y-axis due to
aerodynamic torques (positive nose up)
Mean aerodynamic chord
Mean geometric chord
Aerodynamic normal force along the Z-Body
Axis bu___tpositive up
Yawing moment about Z-axis due to aerodynamic
torques (positive nose right)
Roll rate, angular velocity about X-axis
(positive right wing down)
Pitch rate_ angular velocity about Y-axis
(positive nose up)
2
Dynamic pressure, ]/2 p VTo
Yaw rate_ angular velocity about Z-axis
(positive nose right)
Yaw rate gyro signal
Laplace operator, _+ jw
Reference wing area
Trailing edge
Linear perturbed velocity along the
X-axis (positive forward)
Linear steady-state velocity along the
X-axis (positive forward)
Linear perturbed velocity along the Y-axis
(positive out right wing)
Total linear steady-state velocity
(positive forward)
slugs
ft- ib
ft
ft
ibs
ft-lbs
rad/sec
rad/sec
ibs/ft 2
rad/sec
rad/sec
rad/sec
ft2
ft/sec
ft/sec
ft/sec
ft/sec
A-3
w
W
Wo
X
Y
zj
Z
Linear perturbed velocity along the
Z_-axis (positive do_m)
Weight
Linear steady-st_/Le velocity alonf{ the
Z-axis (positive dovm)
AeroCy_;lamic force along t!_c X-axis
(positive forward)
Aerody_lamic force along Y-axis (positive
out right wing)
Perpendicular distance from c.g. to thrust
line (positive for nose up pitching moment
due to thrust)
Aerodynamic force along Z-axis (positive
down)
ft/sec
lbs
;l't/sec
ibs
_]0s
ft
ibs
_o
Pert_irbed angle of attack
Steady-state (trim) angle of attack
rad
(leg
7o
8a
_e
A
e
Sideslip angle
Steady-state flight path angle
Aileron control surface deflection,
(includes spoiler effects, etc.), (positive
for positive rolling moment)
Elevator surface deflection from trim_
(positive for nose down pitching moment
for aft surface)
Trim elevator deflection
Rudder deflection Ipositive for nose
F
left yawing moment (negative N)]
Denominator of airframe transfer function
Damping ratio of linear second order mode
particularized by the subscript
Pitch angle, fq dt for straight and
level flight, positive nose up
A-4
rad
deg
tad
rad
deg
rad
rad
_o IncJ.ination of thrust line with X-axis
[positive gives negative (--) Z force]
Mass density of air
The real portion of the complex variable
s = _± j_
Roll angle, (cos @o _P dt -sin e o _r dt)
in straight and level flight, (positive
right wing down)
Undamped natural frequency of a second order
mode, particularized by subscript
deg
slugs/ft3
rad/sec
rad
rad/sec
Special Subscript
a
d
e
P
r
R
s
sp
Aileron
Dutch roll
Elevator
Phugoid
Rudder
Roll subsidence
Spiral
Short period
A-5
3, NONDIMENSIONAL DERIVATIVE DEFINITIONS
a) Longitudinal Body Axis
N
CN = _-_ , positive up
X
CX = _ S ' positive aft
c_ : _CN/_
2VT o
CN_ - c bc_/_
CNs : _c_/_s
cxa : 8Cx/_
CxM : _Cx/_M
cxs = 8cx/_s
IV[CM -
Sc
c
2VT o- _cM/_qCMq c
b) Longitudinal Stability Axis
LCL - _ positive up
qS'
DCD - _ positive aft
qS'
Ci_ = _CL/_
2VT o
CI_ - C _Cn/_
CLM = _CL/_M
Cr_ : _C_/_
CDc : _CD/a_
CI_ : _CD/_M
CD5 = _CD/_5
A-6
Pitching moment
derivatives are
identical to
those for body axis
c) Lateral Body and Stability Axis
Thoughphysically and numerically different_* see Appendix B, the
samesymbols are used for body axis and stability axis lateral rolling
and yawing momentderivatives. The sideforce derivatives (Cy, etc.) arephysically and numerically the same in both axis systems. Whenthe
rolling or yawing momentderivatives are given in this report the axis
system is specified. Whenusing the following all quantities should be
for the sameaxis system.
YCy - _s
Cy_ = _Cy/_
Cy_ = _Cy/_
L N
Cl - _Sb Cn - {Sb
CI_ = _CI/_ Cn_ = _Cn/_ _
2v ° _ 2v °CIp - b Cnp b
2VTo _Cl/_r 2VTo _c_/_rClr - b Cnr - b
Cl8 = _Cx/_ cn_ = 8Cn/8_
*The exception is the zero trim angle of attack condition.
A-7
4. DIMENSIONAL STABILITY DERIVATIVE DEFINITIONS
The same symbols are used for body- and stability-axis dimensional
derivatives. Care should be exercised so that a consistent set of
quantities are used.
a) Longitudinal Body Axis
X{_ = Xu + mu cos_o I/sec
pSUo ( M Wo )Xu - - _ CXM - CX + _ CX_ I/secm 2U o '
I Wo MXw _ 0SU2mO - CX_ - 2 U_o (Cx _ -2 CXM)
oSVT2o
X_e = _ CX_ e
]/sec
ft
osec'-rad
Z_ - Su - Tu s:i.n[ o
OSUo M _ CN + CN_Zu - m - _ CNM
p uo[woI M )]Zw - 2m -CNc_ - _ _oo CN 4. _ CNM
p2_ U o
Z_ : - 4m VTo CN&
0SV_ o
CN6 eZSe = - _n
I/sec
] / S (-:_C
]/sec
ftrb
see' r:Ad
Zjm
sec-ft
k-8
Nil - OScU° I_21y Cram + Cm - 2U----o
I 1- 2Iy Cmo_ + _ (Cm + _ CraM)
pSc2 Uo
= C__ _zy V_o
I_ : UoM w
= UoM_
pS C2VTo
Mq - 41y Cmq
oS CV2o
M6e - 21y Cm_e
sec-ft
sec-ft
sec-ft
]/sec 2
]/sec
]/sec
I/sec 2
]/sec
b) Lateral Body Axis
Yv : (oSVTo/2m)Cy _
Y_ = VToY v
Y_ : (pSV_omm)%5
Ys_ : (0SV_o/2m)%%
Y6_ : (pSVTo/2m)dy6r
_B : (_SV_ob/2_x)C__
= (pSVTob2/4Z_)Clp
Lr = (oSVTob2/41x)Clr
]/sec
ft/sec 2
ft/sec 2
ft/sec 2
I/sec
]/sec 2
]/sec
]/sec
A-9
2
_5_ = (oSV_ob/21_)Clb
_r = (oSV$ob/21xlCl_r
Y_a = (oSV_o/2m)CYS_
_ = (oSV$ob/2I_IC__
Np = (oSV_ob2/_Iz)c_.P
Nr = (oSVTob2/41z)Cn r
N_ -- (pSV$ob/2Zz)C__F]
N_ = (_SV_ob/21_)c__
Lt_r = (L_ r + IxzNSr/Ix)G
],t_ : (L_ a + lxzNSa/Ix)@
N' : (N@ + IxzL_/Iz)G
N_ : (Nr + IxzLr/Iz)G
_!_' ( _ IxzLSr/Iz) G" r : N_r
_q : (_ + I_z_/z_)_
1G -
IIxlz
I/sec 2
I/sec 2
l/sec
I/sec 2
I/sec
I/sec
l/sec 2
I/sec 2
I/sec 2
I/sec
]/see
/sec 2
]/sec 2
]/sec 2
I/see
]/sec
]/sec 2
]/sec 2
A-tO
I
--4©_I
Cx
CN
J
./_ Xe, Uo
_a_o_ Ys---Ye
Zs,WoZs
U o = VToCOS a o
Wo = VToSln _o
I
ON = C L cos ao+ C D sin _o
C X = C D cos _o- CL sin Go
CN_ = CL_c°s _o-CLsln ao+ CD_Sln ao+ CD cos ao
CN& = CL_ cos _o
CNM = CLM cos Go + CDM sin _o
CN8 = Ci6 cos Go+ CD5 sin _o
CX_ = CD_ cos _o'CD sin o_-CL_ sin _o-CL cos _o
CXM = CDM cos _o- CL M sin <_o
CX 8 = CD5 cos _o- C_ sin _o
Cm, Cm_ , Cm_ , Cmq , Cram , Cm_ -t_NCHANGED
(C_)B :
(c_;)B =
(Clr) B =
(c_)_ =
(end) B =
(c_)B =
(Cnr) B =
(c_)_ =
C16 cos _o" C_ sin a b
CIp cos£ao - (Clr+ Cnp)Sln ae c_ _o+ Cnr sin2ao
C1 r ces!_e - (C_ r -Clp)sin _e cos &o" Cn F sin2_o
C16 cos a o- Cn_ sin a e
Cn_ cos ao+ CI_ sin a e
Cnp cos2_o - (Cn r-clp)sin _e cos &o'CI r sinlAe
Cnr coS2ao + (Clr+ C_p)sin o_ cos _o + Cip sin_%e
Cn6 cos ao+ CI_ sin a e
Cy_, CYSr , CYsa - t_CHANDEP
y
.L
APPENDIX C
EQUATIONS OF MOTION, TRANSFER FUNCTIONS,AND COUPLING NUmeRATORS
]
I • Longitudinal
a. E quat ion s
s-X_
-4
-X w Wos+g cos ej
(1-Z_)s-Z w -Uos+g sin 80
--(M_s * Mw) s2- MqS -
u XSe
w = Z6e
@ M6 e
q. = -se
}_ = --w cos @o + u sin eo + (U o cos eo + w o sin eo)e
az = sw- Uoq + (g sin eo)e
' ixS2@a z -- az
b. Transfer Functions
@ N_e
5 e A
I) Denominator, A = As 4 + Bs 3 + Cs 2 + Ds + E
A --
B = --(Mq + Xu)(I -- Z_) - Zw - Mc_
c = MqZ w- Mc_ + Xu[(Mq)(1 -- Z_) + Zw + M_]
-- XW_ + WO[M_Z u + _(I -- Z_)] + g_ sin @O
C-I
2)
t
D ---x_(Mz_-_.h)-M_y=+MqK_z_+g[%z_+M_(I-z,_oos0o+Wo(ti>_-t_Iz_)
+ g(%-%x_)_inOo
E --g(MwZ_ -M_Z_)ooseo+ g(M_IXw- %X_)_i_Oo
5 _umerator s
N_ = Aes 2 + Bes + Ce
Ao --z_ + M_(1 - z_)
B 8 = XS[M_Z_+ Mu(1 - Z_.)]+ Zs(Mw-I%X _) -MS[Zw+ XI_(I - ZQ)]
% -"x8(_vz_i-M_zw) + z_,(M_x_-_)+ _,%(zj,_- x_,u)
N_ = Aus 3 + Bu s2 + CuS + Du
A u = X5(I - Z.)w
Bu = -XS[Mq(I - ZQ) + Zw + M_] + ZsX w - Wo[ZsM _ + _o(I - ZQ)]
Cu--x_(M_z.-vh)-z_(g% oos0o+Mqx_)+_%[_- (_ oo_eo)(1-z,)]
+ Wo(ZwM_-_) + _x_% _i._o
Du : g(ZwM5 - MwZs)c°s 00 + g(XsMw - Ms_psin _o
N_ = Aw s3 + Bw s2 + CwS + Dw
Aw= Z6
Bw = -%(Mq+ x_)+ Uo_ + x_z_
Cw = X_(ZsM q - UoMs) + Wo(ZsM u - MsZ _) - gM 5 sin 00 + Xg(M_Uo - Z_Mq)
D w " g(ZJ_ - %Z_)cos 0 o + gMsX* sin 0 o- XsMug sin 0 o
C-2
N_ = A_s 3 + B6s 2 + C_s + D_
A_ = - cos eoAw + sin 0oAu
= - COS @OBW + sin @OBU + (U O cos eO + W O sin 0o)A @
O_ = - cos @OOw + sin eoC u + (U O cos @o + No sin 0o)B @
D_ = - cos @oDw + sin eoD u + (U O cos eO + W O sin eo)C @
.t
_f'= _a[?+B_'zS3+c4__+_ab+E'&z
Ba_ = Bw - ixB e - UoA 0
Ca_ = Cw - ixC e - UoB 0 + g sin @oAe
Da_ = D w - UoC e + g sin 0oB e
Ea_ : + g sin 0oC 8
To obtain az, let ix = O.
2. Lateral
a. Equations
Wos + g cos 0o
s- Yv -VT o
!
--I_ S(S--%)
-._ -._
Uos-g sin 8o] E-
- _o _ IF--L r =
!
s-N r _
Y5 a Y5 r
! !
L5 a L5 r
iNsa ,N5 r
v : VTo _
: _p_ + _r tan DOS S
] r
COS 8 0 S
!
sv + Uor --WoP- g(cos 8o)C_
ay + iXlat sr -- izS p
c-3
b. Transfer Functions
___= N_a r N_r
_a Alat ; _r - Alatetc.
4 2I) Denominator, Ala t = as + bs 3 + cs + ds + e
a = I
!
b = -(y_+ L_+Nr)
U o WoL _o ---- N_+ L_(Y_+_) - N_L_+Y_
VT o VT o
U o
d _ --(_- _) +Yv(_9_r-_) _ (_ cos0°VT o VT o
Wo
VT o
e = -_g [(I%N_- N_I$) cos eo- (N_- L_) sin 0o]VT o
+ N_ sin Oo)
2) 8 (5a or 5r) Numerators
= _s 3 + _s 2 + c_s + D_
A_ : Y_
B_
c_ --
---Y_[_"+N_]- N___Uo+__w°L_'VT o VT o
, U oY_(_'_-_r) +L_--gco__o+(%_ -%_)
VT o VT o
Wo , , , , , g
+ -- (NgL r -- LgNr) + N_ V_T sin 0oVTo o
D6 = -_g (N_L r -- L_Nr) cos 0o + -_g (N_I,_ -- N_I_) sin 0oVT o VT o
c-4
[__ • •
N_5 = Ap s3 + Bp s2 + Cps + Dp
!
Ap = L 5
= LS(Nr + Yv) + NSLr- , , ,,
. , , , , UO
Cp = Y_(LrN _ -- L_N'r) + L_YvN'r -- NsYvLr + (L_N_ -- N_L_) VT °
Dp - VTo
A r = N_
N_ = Ar s3 + Br s2 + Crs + D r
* T ! ! T
Wo , ,
Cr Y_(I,_N_- N_%)- L_YvN _ + N_YvL _ +- (LsN_ -- N_L_)= VTo
Dr VTo
N_ = Acs 2 + Bcs + C
A¢ : Ap + A r tan 6)o
Be : Bp + Br tan 8o
C¢ : Cp + C r tan 8o
c-5
N_ A' s4 C_ys2= ay + B_ s3 + + D_s + E'ay
ay VToA_ + iXlatAr izAp
B'ay = VToB_ + UoAr -WoAp + iXlatBr - IzBp
C_ = VToC _ + UoB r -- WoB p - g cos QoA¢ + iXlatC r - izCp
D ! VT D_ + UoC r - WoC p - g cos 0oB ¢ + iXlatD r - izD po
UoD r- WoD p- g cos eoC ¢
To obtain ay, let Ixlat = i z = O.
c-6
